Results
85-01-01: 85-01-01 BEECH: Amendment 39-4974. Applies to Models 65-88 (S/Ns LP-1 through LP-26, LP-28, and LP-30 through LP-47); 65-90, 65-A90, B90, and C90 (S/Ns LJ-1 through LJ-680); E90 (S/Ns LW-1 through LW-178); 100 and A100 (S/Ns B-1 through B-226); and B100 (S/Ns BE-1 through BE-8) certificated in any category in which all cast acrylic windows have not been replaced with stretched acrylic windows. Compliance: Required as indicated, unless already accomplished. To prevent failures of a cast acrylic window and resulting decompression and possible occupant injury, accomplish the following: (a) Within 50 hours time-in-service (TIS) after the effective date of this AD or 300 hours TIS after the last inspection per AD 81-12-01 whichever occurs later, and each 300 hours TIS thereafter, and within 50 hours TIS after any stripping and repainting in the area of the window; (1) Visually inspect each cast acrylic window in accordance with Beech Service Bulletin No. 2011 (SB2011). (2) If the above inspection discloses any crack, fissure, stress craze or scratch in any window, prior to further pressurized flight, replace this window with a stretched acrylic window of the appropriate part number specified in Paragraph (b). (b) Within one calendar year after the effective date of the AD, replace each cast acrylic window with one of the stretched acrylic windows listed below. WINDOW BEECH PART NUMBER Oval, baggage area 50-440014-837 or -838 Cockpit, side, standard 50-420066-317 or -318 Cockpit, side, oversize 50-420066-353 or -354 Round, Cabin 50-420013-1053 NOTE: After installing a stretched acrylic window make an appropriate entry in the Aircraft Maintenance Record which, along with previous entries, clearly shows each location at which a stretched acrylic window has been installed. (c) Upon installation of all stretched acrylic windows per Paragraph (b), this AD is no longer applicable. (d) Compliance with Paragraphs (a) and (b) is not required if the pressurization system is deactivated as follows, and the aircraft is operated in accordance with this limitation: (1) Secure the "Test/Dump" switch in the "Dump" position; and (2) Fabricate a placard, "CABIN PRESSURIZATION PROHIBITED" of 3/16-inch or larger letters and install it on the control panel adjacent to pressurization system controls; and (3) Insert a copy of this AD in the "Limitations" section of the airplane flight manual. (4) Make an appropriate entry in the Aircraft Maintenance Record showing compliance with this paragraph. (5) The provisions of this paragraph may be accomplished by the holder of at least a private pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person, provided the airplane is not used in air carrier service. (e) Aircraft may be flown unpressurized in accordance with FAR 21.197 to a location where the inspections/repairs required by this AD can be performed. (f) An equivalent method of compliance with this AD may be used when approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas 67209; telephone (316) 946-4400. This AD supersedes AD 81-12-01, Amendment 39-4126. This amendment becomes effective February 6, 1985.
47-02-07: 47-02-07 CULVER: (Was Service Note 1 of AD-778-2.) Applies to Models V and V2 Aircraft. Inspection required after each 100 hours of operation. Inspect landing gear retraction system to determine that adjustments are as follows: (1) With the landing gear extended and no load on the wheels, the push-pull rod adjustments should be such that the center joint of the retraction links attached to each shock strut will withstand a minimum upward pressure of 25 pounds without movement. (2) The length of the push-pull rods in the wing should be so adjusted that the retraction links attached to both main gear struts are under equal pressure. (3) The down limit switch should be adjusted to cut off when the gap between the down stop and the horn on the actuating mechanism is 0.015 inch to 0.020 inch. Maintenance of these adjustments is necessary to prevent damage to the retraction system. (Culver Service Memorandum No. 12 dated November 27, 1946, covers this same subject.)
2021-12-06: The FAA is adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS-365N2, AS 365 N3, SA-365N, and SA-365N1 helicopters. This AD requires replacing the main gearbox (MGB), or as an alternative, replacing the epicyclic reduction gear module for certain serial numbered planet gear assemblies installed on the MGB. This AD also requires inspecting the MGB magnetic plugs and oil filter for particles. Depending on the outcome of the inspections, this AD requires further inspections and replacing certain parts. This AD was prompted by failure of an MGB second stage planet gear. The FAA is issuing this AD to correct an unsafe condition on these products.
77-17-02: 77-17-02 MCDONNELL DOUGLAS: Amendment 39-3015. Applies to DC-10-10, -10F, -30, -30F and -40 series airplanes, certificated in all categories. \n\n\tCompliance required as indicated. \n\n\tTo reduce the probability and severity of an inadvertent engagement of the autopilot actuators, accomplish the following: \n\n\ta.\tWithin 300 additional hours flight time, or thirty days from the effective date of this AD, whichever occurs earlier, unless already accomplished, modify the -5 or earlier pitch guidance control panels, P/N's 3759027, 3759028, 3759029 or 3759050, in accordance with McDonnell Douglas Alert Service Bulletin A22-96, Revision 1, dated July 8, 1977, or later FAA approved revisions. For panel modification and testing, the Douglas Alert Service Bulletin A22-96 refers the modifier to Bendix Alert Service Bulletins A3759027-5-SB7, A3759028-5-SB-7, A3759029-5-SB7 and A3759050-5-SB5 which are embodied into one document dated June 3, 1977. Approval of the Bendix Service Bulletinsis delegated to the Bendix Corporation by the FAA via the TSO system. Approval for incorporation into the DC-10 is via the Douglas Alert Service Bulletin A22-96. For this AD, revisions to the Bendix Bulletins referred to herein must be approved by revisions of Douglas Service Bulletin A22-96. \n\n\tb.\tProduction equivalents or equivalent modifications may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tc.\tSpecial flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to a base for accomplishment of the modification required by this AD. \n\n\tThis amendment becomes effective August 22, 1977.
71-05-07: 71-05-07 AIRESEARCH: Amdt. 39-1166 as amended by Amendment 39-1180 and 39-1277 is further amended by Amendment 39-1430. The AiResearch Manufacturing Company of Arizona. Applies to Turbopropeller Engines Model TPE331-1, -2, -25, -29, -43, -45, -47, -49, -51, -55, -57, -61 and -71 installed in, but not limited to the Mitsubishi MU-2, Swearingen Merlin 2B, Volpar Turboliner and Short Skyvan Aircraft. Compliance required as indicated. To prevent possible failure of the high speed pinion assembly, accomplish the following: (a) Within 50 hours time in service after the effective date of this amendment to AD 71-05-07, as amended, unless already accomplished, and at intervals not to exceed 50 hours time in service thereafter, perform a visual inspection of the engine oil filter per AiResearch Service Bulletin 628, Revision 2, dated March 23, 1972, or later FAA-approved revision, or an equivalent inspection approved by the Chief, Aircraft Engineering Division, FAA Western Region. Return a sample of engine oil and the used engine oil filter element after each inspection to AiResearch for laboratory examination in accordance with AiResearch Service Bulletin 628, Revision 2, dated March 23, 1972, or later FAA-approved revision. Use of other laboratory facilities requires the approval of the Chief, Aircraft Engineering Division, FAA Western Region. Operators must submit substantiating data to obtain this approval. (1) If excessive oil contamination in the filter is found during the visual inspection required in (a) above, the cause must be determined and corrected before further flight. (2) Prior to operation of the engine in excess of 50 hours time in service since the inspection prescribed in (a) above, the owner or operator must receive written confirmation of the results from AiResearch, or another approved facility. (b) Within 50 hours' time in service after the effective date of this AD, unless already accomplished, revise the normal procedures section of the applicable FAA approved Airplane Flight Manuals for aircraft equipped with AiResearch Model TPE331-1, -2, -25, -29, -43, -45, -47, -49, -51, -55, -57, -61, and -71 series engines to include a cautionary note to read as follows: "If sudden loss or significant fluctuation of torque pressure indication occurs, the engine should be promptly shut down and the cause determined before further operation." (c) After the effective date of this amendment to AD 71-05-07, as amended, unless previously accomplished, incorporate, at the next engine overhaul, the improved high speed pinion and thrust washer assembly per AiResearch Service Bulletin 632, Revision 1, dated March 23, 1972, or Service Bulletin 659, Revision 1, dated March 23, 1972, or later FAA-approved revision(s), or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. Upon completion of this modification the inspections of (a) above may be discontinued, and the AFM revision required by (b), above, may be deleted. Amendment 39-1166 became effective on March 9, 1971. Amendment 39-1180 became effective on April 6, 1971. Amendment 39-1277 became effective on September 2, 1971. This Amendment 39-1430 becomes effective on April 8, 1972.
2003-16-04: This amendment adopts a new airworthiness directive (AD) that applies to Pratt & Whitney Canada (PWC) engine models PW118, PW118A, PW118B, PW119B, PW119C, PW120, PW120A, PW121, PW121A, PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G turboprop engines. This amendment requires replacing certain Stewart Warner part number (P/N) fuel heaters, installed on PWC engines, with redesigned fuel heaters. This amendment is prompted by several field incidents in which one or more of the three studs that attach the fuel filter bowl to the fuel heater have been partially or completely pulled free of the fuel heater housing. We are issuing this AD to prevent the separation of the fuel filter bowl from the fuel heater, which could result in a pressurized fuel leak and possible engine fire.
2015-19-04: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 757 airplanes. This AD was prompted by reports of latently failed fuel shutoff valves discovered during fuel filter replacement. This AD requires revising the maintenance or inspection program to include new airworthiness limitations. We are issuing this AD to detect and correct latent failures of the fuel shutoff valve to the engine and auxiliary power unit (APU), which could result in the inability to shut off fuel to the engine and APU and, in case of certain fires, an uncontrollable fire that could lead to structural failure.
88-22-02: 88-22-02 MESSERSCHMITT-BOLKOW-BLOHM (MBB): Amendment 39-6043. Applies to Model BK-117A-1, BK-117A-3, and BK-117A-4 helicopters, all serial numbers, certificated in all categories, equipped with Lycoming Model LTS-101 series engines (Docket 87- ASW-61). Compliance is required within the next 50 hours' time in service after the effective date of this AD, unless already accomplished. To provide the flightcrew with emergency engine shut down instructions to be followed in event of an impending engine turbine burst, insert the following updates (or the forthcoming permanent equivalent revisions) into the applicable FAA-approved flight manual. (a) For the Model BK-117A-1 and BK-117A-3 helicopters, insert into the applicable Rotorcraft Flight Manual--MBB Temporary Revision 5, dated July 27, 1987. (b) For the Model BK-117A-4 helicopter, insert into the applicable Rotorcraft Flight Manual--MBB Temporary Revision 1, dated July 27, 1987. (c) Upon request, an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Directorate, Aircraft Certification Service, ASW-100, FAA, Fort Worth, Texas 76193-0100. This amendment, 39-6043, becomes effective November 16, 1988.
99-22-13: This amendment adopts a new airworthiness directive (AD), applicable to BHTC Model 407 helicopters, that requires visually inspecting the vertical fin (fin) for reduced skin thickness; repairing or replacing the fin, if necessary; and identifying fins that have been inspected or repaired. This amendment is prompted by a report of an inboard skin damaged during production. The actions specified by this AD are intended to detect fin assemblies with reduced skin thickness which, if not corrected, reduce the strength of the skin and could lead to failure of the fin and loss of control of the helicopter.
2015-17-19: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD was prompted by fuel leaks caused by damage to the fan case low-pressure (LP) fuel tube. This AD requires inspection of the fan case LP fuel tubes and associated clips and the fuel oil heat exchanger (FOHE) mounts and associated hardware. We are issuing this AD to prevent failure of the fan case LP fuel tube, which could lead to an in-flight engine shutdown, loss of thrust control, and damage to the airplane.
98-11-29: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 series airplanes and Model Avro 146-RJ series airplanes, that requires a one-time inspection to detect corrosion of the threads of the eyebolt and piston rod on the retraction jack of the main landing gear (MLG); and repair, if necessary. 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 corrosion of the threads of the eyebolt and piston rod on the retraction jack of the MLG, which may cause the eyebolt to detach from the jack, and consequent unrestrained MLG deployment or inability to retract the MLG.
89-25-02: 89-25-02 BOEING: Amendment 39-6402. Docket No. 89-NM-225-AD. \n\n\tApplicability: Model 737-300 and -400 series airplanes, identified in Boeing Alert Service Bulletins 737-77A1026, Revision 2, dated October 27, 1989, and 737-77A1025, dated October 12, 1989, certificated in any category. \n\n\tCompliance: Required within 60 days after the effective date of this AD, unless previously accomplished. \n\n\tTo reduce the risk of engine flameout during inadvertent airplane immersion into thunderstorm activity, accomplish the following: \n\n\tA.\tFor Model 737-300 series airplanes: Modify the engine idle circuitry in accordance with Boeing Alert Service Bulletin 737-77A1026, Revision 2, dated October 27, 1989. \n\n\tNOTE: This action is in addition to the actions required by AD 88-13-51 R1, Amendment 39-6088, for the Model 737-300 series airplanes. \n\n\tB.\tFor Model 737-400 series airplanes: Modify the engine idle circuitry in accordance with Boeing Alert Service Bulletin 737-77A1025, dated October 12, 1989. \n\n\tC.\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 will either concur or comment, and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tD.\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 information from the manufacturer may obtain copies upon request to Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. \n\n\tThis amendment (39-6402, AD 89-25-02) becomes effective on December 11, 1989.
2025-01-05: The FAA is superseding Airworthiness Directive (AD) 2022-25- 07, which applied to all Embraer S.A. Model ERJ 170-100 LR, -100 STD, - 100 SE, and -100 SU airplanes; and Model ERJ 170-200 LR, -200 SU, -200 STD, and -200 LL airplanes. AD 2022-25-07 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 all actions in AD 2022-25-07 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, and certain structural modifications, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2015-18-05: We are superseding Airworthiness Directive (AD) 97-07-14, for certain Airbus Model A320-111, -211, and -231 airplanes. AD 97-07-14 required modification of an area on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings. This new AD continues to require modifying the rib flange on the front spar of the wing center section by installing shims and new fasteners to reinforce pressure floor fittings; and requires repetitive high frequency eddy current inspections for cracking of the radius of the rib flanges and vertical stiffener at frame 36, a rototest inspection for cracking of the fastener holes of the rib flanges, repair if needed, and adding additional airplanes to the applicability. This AD was prompted by the need for repetitive inspections on airplanes on which the modification of the rib flange on the front spar of the wing center section has been done. We are issuing this AD to prevent fatigue cracking on the rib flange area of the front spar of the wing center section, which can reduce the structural integrity of fuselage frame 36 and the wing center section.
98-25-14: 98-25-14 Rolls-Royce plc: Amendment 39-10940. Docket 98-ANE-06-AD. Applicability: Rolls-Royce plc (R-R) Viper Mk. 521, 522, 526 and 601 series turbojet engines, installed on but not limited to Raytheon (formerly British Aerospace, Hawker Siddeley) Models BH.125 and DH.125 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For engines that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent a high pressure fuel leak, which could result in an engine nacelle fire and damage to the aircraft, accomplish the following: (a) For R-R Viper Mk. 521, and 522 series engines, perform a one-time inspection of the barometric flow control unit (BFCU) augmentor and bypass valve joint washer for joint washer integrity, and replace, if necessary, with serviceable parts, in accordance with R-R Alert Service Bulletins (ASBs) Nos. 73-A120 and 73-A121, as applicable, dated November 1997, as follows: (1) For engines with less than 200 hours time in service (TIS) since new, overhaul, or repair of the BFCU, inspect within 2 months, or 100 hours TIS after the effective date of this AD, whichever occurs first. (2) For engines with 200 or more hours TIS since new, overhaul, or repair of the BFCU, inspect at the next engine removal after the effectivedate of this AD. (b) For R-R Viper Mk. 526 series engines, perform a one-time inspection of the barometric flow control unit (BFCU) augmentor and bypass valve joint washer for joint washer integrity, and replace, if necessary, with serviceable parts, in accordance with R-R ASBs Nos. 73-A68 and 73-A69, as applicable, dated November 1997, as follows: (1) For engines with less than 200 hours time in service (TIS) since new, overhaul, or repair of the BFCU, inspect within 2 months, or 100 hours TIS after the effective date of this AD, whichever occurs first. (2) For engines with 200 or more hours TIS since new, overhaul, or repair of the BFCU, inspect at the next engine removal after the effective date of this AD. (c) For R-R Viper Mk. 601 series engines, perform a one-time inspection of the BFCU augmentor and bypass valve joint washer for joint washer integrity, and replace, if necessary, with serviceable parts, in accordance with R-R ASBs Nos. 73-A35 and 73-A36, as applicable, dated November 1997, as follows: (1) For engines with less than 200 hours TIS since new, overhaul, or repair of the BFCU, inspect within 2 months, or 100 hours TIS after the effective date of this AD, whichever occurs first. (2) For engines with 200 or more hours TIS since new, overhaul, or repair of the BFCU, inspect at the next engine removal after the effective date of this AD. (d) 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, Engine Certification Office. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (e) Special flight permits may beissued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the aircraft to a location where the requirements of this AD can be accomplished. (f) The actions required by this AD shall be done in accordance with the following R-R ASBs: Document No Pages Date 73-A35 1-6 November 1997 Total Pages: 6. 73-A36 1-6 November 1997 Total Pages: 6. 73-A68 1-6 November 1997 Total Pages: 6. 73-A69 1-6 November 1997 Total Pages: 6. 73-A120 1-6 November 1997 Total Pages: 6. 73-A121 1-6 November 1997 Total Pages: 6. 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 Rolls-Royce Limited, Bristol Engines Division, Technical Publications Department CLS-4, P.O. Box 3, Filton, Bristol, BS34 7QE England; telephone 117-979-1234, fax 117-979-7575.Copies may be inspected at the FAA, New England Region, Office of the Regional Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on February 12, 1999.
97-06-11: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) 35 series airplanes (formerly referred to as Beech 35 series airplanes). This action requires inspecting the ruddervator differential tail control rod assembly for corrosion or cracks, repairing or replacing any cracked or corroded part, and applying anti-corrosion sealant to the ruddervator control pushrods. This action results from a report of a split in the ruddervator control push rod on an affected airplane that was found during a routine inspection. The split occurred when water froze in the internal area of the control push rod and then expanded. The actions specified by this AD are intended to prevent failure of the differential tail control rod assembly, which could result in loss of control of the airplane.
2025-02-13: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200, -200CB, and -200PF series airplanes. This AD was prompted by a report indicating an operator has found cracks on three Model 757-200PF airplanes at the main deck cargo door cutout forward and aft hinge attachment holes. This AD requires a maintenance record check for repairs at the forward and aft hinge areas of the main deck cargo door cutout; repetitive open-hole high frequency eddy current (HFEC) inspections for cracks in the unrepaired areas of the bear strap, skin, doubler, and upper sill chord at the main deck cargo door forward and aft hinge attachment holes; and applicable corrective actions. The FAA is issuing this AD to address the unsafe condition on these products.
92-17-09: 92-17-09 BRITISH AEROSPACE: Amendment 39-8338. Docket No. 92-NM-62-AD. Applicability: Model BAe 125-800A series airplanes on which Modification 259283C thrust reversers have been installed, and on which Modification 259949A or BAe Repair Instruction Leaflet (RIL) 25-8ES16 has not been installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent damage that may cause unsymmetrical thrust, accomplish the following: (a) Within 9 months after the effective date of this AD, install Modification 259949A, in accordance with British Aerospace Service Bulletin SB.78-4-9949A, dated January 20, 1992. (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, 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. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (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 modification shall be done in accordance with British Aerospace Service Bulletin SB.78-4-9949A, dated January 20, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, DC. 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., 7th Floor, Suite 700, Washington, DC. (e) This amendment becomes effective on September 28, 1992.
92-02-10: 92-02-10 AEROSPATIALE: Amendment 39-8146. Docket 91-NM-185-AD. Applicability: Model ATR42-200, -300, and -320 series airplanes; Serial Numbers 16, 17, 19, 20, 22 through 34, 36 through 39, 41 through 45, 47 through 49, 54, 59, and 107; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent collapse of the nose landing gear (NLG), accomplish the following: (a) Perform a dye penetrant inspection to detect cracks of the four hinge pins of the left-hand and right-hand NLG leg and drag braces, and accomplish emergency extension functional tests, in accordance with Aerospatiale Service Bulletin ATR42-32-0039, Revision 1, dated August 1, 1991, at the applicable time specified below: (1) For airplane serial numbers 17, 19, 22, 23, 24, 26, 28, 30, 31, 33, 37, 39, 41, 44, 45, 47, 48, and 59: Within 30 days after the effective date of this AD, or prior to the accumulation of 250 hours time-in-service, whicheveroccurs first. (2) For airplane serial numbers 16, 20, 25, 27, 29, 32, 34, 36, 38, 42, 43, 49, 54, and 107: Within 60 days after the effective date of this AD, or prior to the accumulation of 500 hours time-in-service, whichever occurs first. (b) If a cracked hinge pin is found as a result of the inspection required by paragraph (a) of this AD, replace it with a new hinge pin or with a hinge pin that previously has been inspected and found to be free of cracks, in accordance with Aerospatiale Service Bulletin ATR42- 32-0039, Revision 1, dated August 1, 1991. (c) As of the effective date of this AD, no hinge pin shall be installed on any airplane unless that hinge pin is new or has been inspected in accordance with Aerospatiale Service Bulletin ATR42-32-0039, Revision 1, dated August 1, 1991, and found to be free of cracks. (d) An 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it 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 the airplane to a location where the requirements of this AD can be accomplished. (f) The inspection and replacement of hinge pins required by this AD shall be done in accordance with Aerospatiale Service Bulletin ATR42-32-0039, Revision 1, dated August 1, 1991, which incorporates the following list of effective pages: Page Numbers Revision Number Date 1, 12, and 13-14 1 August 1, 1991 2, 3, 4, 5-6, 7, 8, 10, 11, and 15 Blank July 18, 1991 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. (g) This amendment (39-8146, AD 92-02-10) becomes effective on March 2, 1992.
2021-02-20: The FAA is adopting a new airworthiness directive (AD) for all Helicopteres Guimbal Model Cabri G2 helicopters. This AD was prompted by a report of a crack in a rotating scissor fitting. This AD requires an initial and repetitive inspections of certain rotating and non-rotating scissor fittings, and depending on the results, replacing the affected assembly. This AD also prohibits installing certain main rotor hubs (MRHs) and swashplate guides unless the initial inspection has been accomplished. The FAA is issuing this AD to address the unsafe condition on these products.
91-21-13: 91-21-13 BOEING: Amendment 39-8060. Docket 91-NM-80-AD. Supersedes AD's 89-13-05 and 89-23-05. \n\n\tApplicability: Model 737-300, -400, and -500 series airplanes, listed in Boeing Service Bulletin 737-76-1023, dated February 14, 1991, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo minimize the potential for cable separation due to the Number 2 engine throttle cable chafing against the right wing front spar bracket, and to prevent Number 1 and Number 2 engine throttle control cable ratcheting feedback, accomplish the following: \n\n\tA.\tFor Model 737-300 series airplanes: Prior to the accumulation of 300 flight hours after July 24, 1989 (the effective date of Amendment 39-6240), unless previously accomplished within the previous 700 flight hours, and thereafter at intervals not to exceed 1,000 flight hours, gain access to the fuel shutoff cable pulley bracket near the right wing front spar station 124 and inspect thenumber two engine throttle cable for wear. Replace the cable, before further flight, if cable wear exceeds acceptable wear limits specified in Section 20-20-31 of the Model 737 Maintenance Manual. \n\n\tB.\tFor Model 737-400 series airplanes: Prior to the accumulation of 300 flight hours after November 27, 1989 (the effective date of Amendment 39-6367), unless previously accomplished within the previous 700 flight hours, and thereafter at intervals not to exceed 1,000 flight hours, gain access to the fuel shutoff cable pulley bracket near the right wing front spar station 124 and inspect the number two engine throttle cable for wear. Replace the cable, before further flight, if cable wear exceeds acceptable wear limits specified in Section 20-20-31 of the Model 737 Maintenance Manual. \n\n\tC.\tFor all airplanes: Within 36 months after the effective date of this AD, modify the engine throttle control cable system in accordance with Boeing Service Bulletin 737-76-1023, dated February 14, 1991. This modification constitutes terminating action for the repetitive inspections required by paragraphs A. and B. of this AD. \n\n\tD.\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. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \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\tF.\tThe inspections and modifications shall be done in accordance with Boeing Service Bulletin 737-76-1023, dated February 14, 1991. 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 Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\tAirworthiness Directive 91-21-13 supersedes AD 89-13-05, Amendment 39-6240; and AD 89-23-05, Amendment 39-6367. \n\tThis amendment (39-8060, AD 91-21-13) becomes effective on November 29, 1991.
2025-02-02: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD was prompted by a report indicating cracks in the frame inner chord and web at station (STA) 727. This AD requires an inspection for any repair installed, repetitive inspections of the frame inner chord and web at STA 727 for any crack, and applicable on- condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
2003-15-08: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (ECF) model helicopters that requires replacing the main gearbox (MGB) opening neoprene cowling seals (seals) with airworthy glass/silicone seals. This amendment is prompted by the discovery that neoprene seals currently installed on the MGB opening cowlings do not provide the fire protection required by the airworthiness standards. The actions specified by this AD are intended to prevent a fire in the engine compartment from reaching the MGB compartment that contains parts that are not fire resistant and subsequent loss of control of the helicopter.
90-15-01: 90-15-01 ROGERSON HILLER CORPORATION (HILLER, FAIRCHILD HILLER): Amendment 39-6879. Docket No. 90-ASW-39. Final Rule of priority letter AD. Applicability: All Model UH-12E, UH-12E-L, UH-12L, and UH-12L4 series helicopters, certificated in any category. Compliance: Required prior to further flight, unless already accomplished. To prevent failure of a tail rotor blade assembly, which could result in loss of controllability of the helicopter, accomplish the following: (a) Determine the part number and serial number of the tail rotor blade assemblies installed on the helicopter. The serial number is located on a raised rectangular boss on the barrel section of the blade root fitting. (b) If any tail rotor blade assembly installed is P/N 55073 and is identified with any of the serial numbers listed below, regardless of the hours' time in service, remove and replace the blade assembly with an airworthy part before further flight: Serial Numbers: 3028 3089 9506 9584 9607 10245 10516 10917 13278 14715 14898 15073 15285 15978 16114 20918 NOTE: Any unairworthy blade assemblies found as a result of this AD should be permanently marked as unairworthy. (c) If any of the tail rotor blade assemblies listed in paragraph (b) are found, report the helicopter registration number, serial number, and tail rotor blade assembly serial number to the Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, Transport Airplane Directorate, within 10 days of the inspection required by paragraph (a) of this AD. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate helicopters to a base in order to comply with the requirements of this AD. (e) Record compliance with paragraph (b) in the AD compliance record and in the maintenance record of the helicopter log book. This record must include the serial number of any deficient blade assembly foundduring compliance with this AD. (f) An alternate means of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be used when approved by the Manager, Seattle ACO, FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. Note: The request should be submitted directly to the Manager, Seattle ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Seattle ACO. This amendment (39-6879, AD 90-15-01) becomes effective on March 7, 1991, as to all persons, except those persons to whom it was made immediately effective by Priority Letter AD 90-15-01, issued on July 11, 1990, which contained this amendment.
2020-26-16: The FAA is adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. (Piper) Models PA-28-151, PA-28-161, PA- 28-181, PA-28-235, PA-28R-180, PA-28R-200, PA-28R-201, PA-28R-201T, PA- 28RT-201, PA-28RT-201T, PA-32-260, PA-32-300, PA-32R-300, PA-32RT-300, and PA-32RT-300T airplanes. This AD was prompted by a report of a wing separation caused by fatigue cracking in a visually inaccessible area of the lower main wing spar cap. This AD requires calculating the factored service hours for each main wing spar to determine when an inspection is required, inspecting the lower main wing spar bolt holes for cracks, and replacing any cracked main wing spar. The FAA is issuing this AD to address the unsafe condition on these products.