Results
75-27-02: 75-27-02 BRITISH AIRCRAFT CORPORATION: Amendment 39-2474. Applies to British Aircraft Corporation (BAC) Viscount Models 744, 745D and 810 airplanes, certificated in all categories. Compliance is required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. To prevent failure of propeller feathering, install an electrical back-up to the primary manual feathering system in accordance with the instructions contained in BAC Bulletin-For- Modification No. FG.2122, dated February 11, 1972, (for Viscount Model 810 airplanes), or BAC Bulletin-For-Modification No. D.3245, dated February 11, 1972 (for Viscount Models 744 and 745D airplanes), as appropriate, or an equivalent of either approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, FAA-American Embassy, APO New York 09667. This amendment becomes effective on January 19, 1976.
2005-18-23: The FAA is superseding an existing airworthiness directive (AD), which applies to all Boeing Model 737-600, -700, -700C, -800, and -900 series airplanes. That AD currently requires either determining exposure to runway deicing fluids containing potassium formate, or performing repetitive inspections of certain electrical connectors in the wheel well of the main landing gear (MLG) for corrosion, and follow-on actions. This new AD adds a new inspection requirement and related corrective actions. This AD is prompted by additional reports indicating that significant corrosion of the electrical connectors in the wheel well of the MLG has also been found on airplanes that land on runways treated with deicing fluids containing potassium acetate. We are issuing this AD to prevent corrosion and subsequent moisture ingress into the electrical connectors, which could result in an electrical short and consequent incorrect functioning of critical airplane systems essential to safe flight and landing of the airplane, including fire warning systems. \n\n\nDATES: This AD becomes effective October 19, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 737-24A1148, Revision 1, dated July 10, 2003; as listed in the AD; is approved by the Director of the Federal Register as of October 19, 2005.
2016-26-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by reports indicating that certain wing side-of-body upper stringer fittings have been installed with faying surface mismatch beyond the allowed machining tolerance. This AD requires inspections of certain stringer fittings, replacement if necessary, and replacement of certain fasteners. We are issuing this AD to address the unsafe condition on these products.
2016-20-04: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model SA341G and SA342J. This AD prohibits autorotation training flights until the hardness of the landing gear rear crosstube (crosstube) is inspected. This AD is prompted by two reports of crosstubes failing during ground handling. These actions are intended to prevent failure of a crosstube, which could result in dropping or tipping of the helicopter.
83-15-09: 83-15-09 FAIRCHILD (SWEARINGEN): Amendment 39-4702. Applies to the following models and serial numbers of airplanes certificated in any category: Model SA226-T (S/N T-249 through T-275, and T-277 through T-291), Model SA226-TB (S/N T-276 and T-292 through T-417), Model SA226-AT (S/N AT-025 through AT-069, AT-071 through AT-074), Model SA226-TC (S/N TC-212 through TC-419), Any SA226 model and serial number airplane modified in accordance with Service Bulletin SB 32-016, Model SA227-AC (S/N AC-398 through AC-599) and all models with hydraulic nose wheel steering, Model SA227-AT (S/N AT-070, S/N AT-423 through AT-596), Model SA227-TT (S/N TT-421 through TT-597). Compliance: Required as indicated unless already accomplished. To assure reliable operation of the steering system: a) On or before November 1, 1983: 1) Modify the nose wheel steering systems of the affected Serial No. Model SA226-T, SA226-TB, SA226-AT, and SA226-TC airplanes in accordance with Fairchild (Swearingen) Service Bulletin SB 32-037 revised July 15, 1982, or if optional tiller wheel steering is installed, in accordance with SB 32-039 dated September 9, 1982. 2) Modify the nose wheel steering systems of the affected Serial Number Model SA227-AC, SA227-AT, and SA227-TT airplanes in accordance with Fairchild Service Bulletin SB 32-006 revised July 27, 1982. 3) When the modifications required by paragraphs a)1) and a)2) of this AD are accomplished, remove the nose wheel steering operational restrictions in the Limitations Section of the Airplane Flight Manual and placards in the airplane that were incorporated in accordance with Fairchild Swearingen Service Bulletins SBA 32-001 or SBA 32-032 both dated June 3, 1981. b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. c) An equivalent method of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, Federal Aviation Administration, Southwest Regional Office, P.O. Box 1689, Fort Worth, Texas 76101. This amendment becomes effective on September 8, 1983.
2005-18-21: The FAA is adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company Models 1900, 1900C, 1900C (C-12J), and 1900D airplanes. This AD requires you to inspect all elevator hinge support attachments on both left and right elevators for loose and missing rivets, replace rivets if loose or missing rivets are found, inspect the elevator hinge joints for looseness and clearance of each elevator to its stabilizer, correct looseness and clearance if incorrect, and report results of the required inspections. This AD results from a report of excessive movement of the elevator and elevator trim. The hinge support attachment that attaches the elevator to the horizontal stabilizer was loose and had loose and missing rivets. The elevator counterweight horn showed evidence of rubbing against the horizontal stabilizer, indicating possible incorrect clearance. We are issuing this AD to detect and correct any looseness in the elevator hinge support attachments, which could result in binding of the elevator control system. This elevator binding could lead to loss of control of the airplane.
97-25-07: This amendment supersedes an existing airworthiness directive (AD), applicable to GE Aircraft Engines (GE) CT7 series turboprop engines, that currently requires eddy current inspection (ECI) of disk holes of stage 1 and 2 gas generator turbine (GGT) disks for cracks, and, if necessary, replacement with serviceable parts. This amendment increases the initial cyclic compliance threshold while decreasing the calendar time for performing the ECI. This amendment is prompted by corrections to the applicable alert service bulletin (ASB) serial number (S/N) tables. The ASB contained S/Ns which appeared in more than one table creating confusion over which cyclic limit applied to each S/N. The actions specified by this AD are intended to prevent a stage 1 or 2 GGT disk failure, which could result in an uncontained engine failure and damage to the aircraft.
97-11-02 R1: This amendment revises an existing airworthiness directive (AD), applicable to certain British Aerospace (Jetstream) Model 4101 airplanes, that currently requires an inspection to determine the thickness of the intercostal that attaches the third crew member seat to the floor structure in the flight compartment, and replacement, if necessary. That action was prompted by a report from the manufacturer indicating that intercostals have been installed that are not of sufficient thickness (and consequent strength) to support the third crew member seat during emergency landing dynamic conditions. The actions specified by that AD are intended to prevent the failure of this intercostal during an emergency landing, which could consequently result in injury to the flight crew. This amendment revises the applicability of the existing AD by removing several airplanes.
80-18-51: 80-18-51 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 4143. Applies to Model SA-330 series helicopters, certificated in all categories. Compliance required as indicated. To prevent friction between the electrical wires and hydraulic lines, which could result in leakage of hydraulic fluid and possible fire, accomplish the following: Prior to further flight, unless already accomplished within the last 50 hours time in service, inspect the electrical wires and hydraulic lines between fuselage stations 5295 and 5600 for chafing against each other and the airframe, and separate and secure electrical wires and hydraulic lines as necessary to prevent chafing. Any chafed electrical wires or hydraulic lines must be replaced before further flight. Report defects found to the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. (Reporting approved by the Office of Management and Budget under OMB No. 04- R0174.) This amendment becomes effective June 18, 1981, as to all persons except those persons to whom it was made immediately effective by telegraphic AD T80-18-51, issued August 29, 1980, which contained this amendment.
2005-18-18: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757 airplanes. This AD requires inspections of certain wire bundles in the left and right engine-to-wing aft fairings for discrepancies; installation of back-to-back p-clamps between the wire and hydraulic supply tube at the aft end of the right-hand strut only; and associated re-routing of the wire bundles, if necessary. This AD results from a report indicating that a circuit breaker for the fuel shutoff valve tripped due to a wire that chafed against the structure in the flammable leakage zone of the aft fairing, causing a short circuit. We are issuing this AD to prevent chafing between the wire bundle and the structure of the aft fairing, which could result in electrical arcing and subsequent ignition of flammable vapors and possible uncontrollable fire.
2016-26-03: We are superseding Airworthiness Directive (AD) 2013-23-02 for all Airbus Defense and Space S.A. Model CN-235, CN-235-100, CN-235-200, CN-235-300, and C-295 airplanes. AD 2013-23-02 required an inspection of the feeder cables of certain fuel booster pumps for damage (including, but not limited to, signs of electrical arcing and fuel leaks), and replacement if necessary. This new AD retains those requirements and also requires modification of the electrical installation of the fuel booster pumps. This AD was prompted by a report of an in-flight problem with the fuel transfer system. We are issuing this AD to address the unsafe condition on these products.
2016-07-24: We are adopting a new airworthiness directive (AD) for all Textron Aviation, Inc. Models 310 through 310R, E310H, E310J, T310P through T310R, 310J-1, 320 through 320F, 320-1, 335, 340, 340A, 401 through 401B, 402 through 402C, 411, 411A, 414, 414A, and 421 through 421C [[Page 21251]] airplanes (type certificates 3A10, 3A25, and A7CE previously held by Cessna Aircraft Company). This AD requires replacement and repetitive inspections of the hardware securing the elevator trim push-pull rod. This AD was prompted by lessons learned in accident investigation support, analysis of past accidents, and NTSB determinations of probable cause. That information indicates that following the loss of the attachment hardware connecting the elevator trim tab actuator to the elevator trim tab push-pull rod, the elevator tab may jam in a position outside the normal limits of travel. We are issuing this AD to correct the unsafe condition on these products.
98-01-04: This amendment adopts a new airworthiness directive (AD), applicable to all Fokker Model F27 Mark 050 series airplanes. This action requires a one-time inspection of the main landing gear (MLG) locklinks to determine if the lockwire that secures both platform bolts is in one piece and in position; and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent collapse of the MLG due to failure of the locklinks to lock in the down position.
2005-20-35: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A320-111 airplanes. The existing AD currently requires repetitive inspections for cracking in the front and rear faces and at the crown fittings of the upper stringers of the center wing box and applicable repairs. This new AD requires continuing the repetitive inspections at revised thresholds and intervals, and applicable repairs. This AD results from a manufacturer survey of airplanes affected by the existing inspection program that led to the consequent revision of the thresholds and intervals of the repetitive inspections. We are issuing this AD to detect and correct fatigue cracking of the upper stringers of the center wing box, which could lead to loss of structural integrity of the wing.
2002-02-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 707 and 720 series airplanes, that requires installation of a new support structure for the trailing edge beam and main landing gear uplock mechanism. This action is necessary to prevent cracking in the frame and adjacent structure near the attach bolt of the main landing gear uplock mechanism, which could lead to compromised structural integrity. This action is intended to address the identified unsafe condition.
97-26-21: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100, 747-200, 747-300, 747SR, and 747SP series airplanes. This action requires a one-time inspection to detect cracking of the longeron splice fittings at stringer 11, on the left and right sides at body station 2598, and replacement of any cracked fitting with a new fitting. This amendment is prompted by reports that fatigue cracking was found on longeron splice fittings. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in reduced controllability of the horizontal stabilizer.
97-26-06: This amendment adopts a new airworthiness directive (AD), applicable to all EMBRAER Model EMB-120 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the ice protection systems, and to add information regarding operation in icing conditions. This amendment also requires installing an ice detector system and revising the AFM to include procedures for testing system integrity. This amendment is prompted by reports indicating that flightcrews experienced difficulties controlling the airplane during (or following) flight in normal icing conditions, when the ice protection system either was not activated when ice began to accumulate on the airplane, or the ice protection system was never activated. These difficulties may have occurred because the flightcrews did not recognize that a significant enough amount of ice had formed on the airplane to require activation of the deicing equipment. The actions specified bythis AD are intended to ensure that the flightcrew is able to recognize the formation of significant ice accretion and take appropriate action; such formation of ice could result in reduced controllability of the airplane in normal icing conditions.
80-12-14: 80-12-14 PIPER (TED SMITH): Amendment 39-3801. Applies to Aerostar Model 600, 601, 601P Serial Nos. 0001 through 0799 airplanes certificated in all categories. Compliance required as indicated, unless already accomplished. To prevent the reentry of an engine fire into the underwing structure behind the engine nacelle, accomplish the following: (a) Within the next 300 hours' time in service, or ninety days after the effective date of this AD, whichever occurs sooner, install a metal fairing, P/N 230090-1 and -2, in place of the existing fiberglass fairing, P/N 230023-501 and 502, in accordance with Piper Service Bulletin So 600-83, dated November 21, 1979. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. (c) Alternative inspections, modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective June 19, 1980.
2005-18-20: The FAA is adopting a new airworthiness directive (AD) for Goodrich De-icing and Specialty Systems "FASTprop" propeller de- icers, part numbers P4E1188 series, P4E1601 series, P4E2200 series, P4E2271-10, P4E2575-7, P4E2575-10, P4E2598-10, P5855BSW, P6199SW, P6592SW, P6662SW, and P6975-11, installed. This AD requires inspection, repair, or replacement of those "FASTprop" propeller de-icers that fail daily visual checks. This AD results from reports of Goodrich "FASTprop" propeller de-icers becoming loose or debonded, and detaching from propeller blades during operation.
97-26-08: This amendment adopts a new airworthiness directive (AD) that applies to Mooney Aircraft Corporation (Mooney) Models M20F, M20J, and M20L airplanes. This action requires removing the fuel cap retaining lanyard from the fuel filler cap assemblies. A report of lost engine power during flight because of fuel starvation prompted the action. The investigation revealed that the airplane fuel float became trapped by the fuel cap retaining lanyard, keeping the float from following the fuel level. This condition caused the pilot to get a false fuel quantity reading. The actions specified by this AD are intended to prevent loss of engine power and fuel depletion during flight caused by a false fuel gauge reading.
2016-24-51: We are publishing a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-92A helicopters, which was sent previously to all known U.S. owners and operators of these helicopters. This AD requires inspecting certain bearings. This AD is prompted by a report of a failed bearing. We are issuing this AD to address the unsafe condition on these products.
97-26-14: This amendment adopts a new airworthiness directive (AD) that applies to all MAULE Models MX-7-420 and MXT-7-420 airplanes, and all Models M-7-235 and M-7-235A airplanes that are modified in accordance with Maule STC SA2661SO, which incorporates a certain gas turbine engine, certain amphibious floats, and certain propellers. This AD requires amending the Limitations Section of the airplane flight manual (AFM) to prohibit the positioning of the power levers below the flight idle stop while the airplane is in flight. This AFM amendment will include a statement of consequences if the limitation is not followed. This AD results from numerous incidents and five documented accidents involving airplanes equipped with turboprop engines where the propeller beta was improperly utilized during flight. The actions specified by this AD are intended to prevent loss of airplane control or engine overspeed with consequent loss of engine power caused by the power levers being positioned belowthe flight idle stop while the airplane is in flight.
61-21-01: 61-21-01 CANADAIR: Amdt. 348 Part 507 Federal Register October 17, 1961. Applies to Model CL-44D4 Aircraft, Serial Numbers 14, 16, 19 through 23, 25 and 26. Compliance required within the next 25 hours' time in service unless already accomplished within the last 10 hours' time in service and at intervals not to exceed 35 hours' time in service. To preclude failure of the tail pipe door structure, the following must be accomplished: (a) Inspect the following tail pipe compartment access panels for fatigue cracking using dye penetrant or equivalent in the area of the attachment holes. Part Numbers to be inspected are 44-10721, 44-10721-1, 44-10722, 44-10722-1, 44-10726, 44-10721-990, 44- 10721-991, 44-10722-990, 44-10722-991, 44-10726-990, 44-10751, 44-10751-1, 44-10752, 44- 10752-1, and 44-10753. (b) If cracks are found, panels must be replaced, repaired or reinforced in accordance with Canadair Service Bulletin No. CL-44D4-138 or equivalent, or modified in accordance with a Department of Transport and FAA approved modification prior to further flight except ferry flight in accordance with the provisions of CAR 1.76. Following the incorporation of the interim repair or reinforcement covered in Service Bulletin No. CL-44D4- 138, or replacement, the inspections specified in (a) must be continued at intervals not exceeding 35 hours' time in service. If further cracks are found after repair or reinforcement per Canadair Service Bulletin CL-44D4-138, the parts shall be replaced or modified in accordance with Canadian Department of Transport and FAA approved modification. (c) The special inspections required by this airworthiness directive may be discontinued after incorporation of the Canadian Department of Transport and FAA approved modification of the affected parts. (d) Upon request of the operator, an FAA maintenance inspector, subject to approval of the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective October 17, 1961.
71-11-02: 71-11-02 AVCO LYCOMING: Amdt. 39-1208 as amended by Amendment 39-1403. Applies to all IO- 360A and -C Series engines with serial numbers 1734-51A through 4412-51A and all such series engines remanufactured between 1 September 1965 and 11 October 1967. Compliance required as indicated, unless already accomplished. To prevent valve failures replace the intake and exhaust hydraulic tappet plunger assembly P/N 76290 with P/N 78290 at the time in service specified below: (a) Engines with less than 400 hours in service on P/N 76290 as of the effective date of this AD, shall comply prior to the accumulation of 450 hours in service. (b) Engines with 400 or more hours in service on P/N 76290 as of the effective date of this AD shall comply within the next 50 hours in service. (Note: Lycoming Service Bulletin No. 328 covers this subject.) Amendment 39-1208 was effective May 19, 1971. This Amendment 39-1403 is effective March 14, 1972.
2016-26-01: We are adopting a new airworthiness directive (AD) for certain Agusta Model AB139 and AW139 helicopters. This AD requires performing operational checks of both hydraulic systems. This AD was prompted by an assessment of the hydraulic systems of the helicopter following an accident. These actions are intended to prevent the unsafe condition on these products.