Results
59-05-01: 59-05-01 BELL: Applies to All Model 47 Helicopters Having Metal Tail Rotor Blades, P/N's 47-642-102-1; -5; -7; -9; -17; and -19 Installed. Compliance required as indicated. As a result of several cracks having occurred (in most instances following known damage due to the tail rotor striking water, tall grass, or underbrush) the following inspection of the metal tail rotor blades, to preclude loss of tail rotor control, must be accomplished as indicated: (1) On trailing edge of blade, remove paint in the area of Numbers 3, 4, 5 and 6 rivets to the bare metal, with a suitable lacquer thinner only. Feather edges of remaining paint with thinner. DO NOT use sandpaper, steel-wool, or other sharp objects to remove paint. DO NOT use a paint stripper. NOTE: The removal of paint does not affect the balance. (2) Visually inspect for chordwise cracks along the trailing edge of blade, in the area of rivets Numbers 3, 4, 5 and 6 counting from the butt end towards tip end.It is mandatory that the tail rotor blades be replaced if any cracks are found. (3) If no cracks are found, it is mandatory that the bare metal portion of blades be left unpainted to facilitate daily inspection. To protect the bare metal, a thin coat of clear lacquer, cosmolene, or grease shall be applied to the area. (4) Tail rotor blades, installed on float equipped helicopters or which have had any service time on float equipped helicopters, shall be inspected prior to each flight. (5) Tail rotor blades installed on helicopters not operated on floats shall be inspected daily. (Bell Service Bulletin No. 128SB, dated January 27, 1959, covers the same subject.)
2005-19-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes. This AD requires repetitive inspections of the dual side braces (DSBs), underwing midspar fittings, and associated parts; other specified actions; and corrective actions if necessary. This AD also provides an optional terminating action for the inspections and other specified actions. This AD is prompted by reports of corroded, migrated, and rotated bearings for the DSBs in the inboard and outboard struts, a report of a fractured retainer for the eccentric bushing for one of the side links of a DSB, and reports of wear and damage to the underwing midspar fitting on the outboard strut. We are issuing this AD to prevent the loss of a DSB or underwing midspar fitting load path, which could result in the transfer of loads and motion to other areas of a strut, and possible separation of a strut and engine from the airplane during flight.
2017-04-01: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model GVI airplanes. This AD was prompted by a report indicating that there are design deficiencies in the software used for monitoring the disconnect for the flight control computer (FCC)-hosted flight controls actuation main ram linear variable differential transducer (LVDT). This AD requires an update of the FCC software. We are issuing this AD to address the unsafe condition on these products.
2016-24-08: We are adopting a new airworthiness directive (AD) for all \n\n((Page 86568)) \n\nRolls-Royce plc (RR) RB211-Trent 875-17, RB211-Trent 877-17, RB211- Trent 884-17, RB211-Trent 884B-17, RB211-Trent 892-17, RB211-Trent 892B-17, and RB211-Trent 895-17 turbofan engines. This AD requires repetitive inspections of the engine upper bifurcation fairing and repairing or replacing any fairing that fails inspection. This AD was prompted by a report of cracking and material release from an engine upper bifurcation fairing. We are issuing this AD to prevent failure of the engine fire protection system, engine fire, and damage to the airplane.
63-03-02: 63-03-02 CANADAIR: Amdt. 533 Part 507 Federal Register February 6, 1963. Applies to all Model CL-44D4 aircraft. Compliance required as indicated. As a result of failure of a riveted rudder lower balance weight, the following must be accomplished: (a) Prior to each departure from the principal maintenance base, inspect the rudder bottom closing rib for any indication of a balance weight becoming detached and dropping on to the rib. If so found, repair per (c) prior to further flight. (b) Within the next 35 hours' time in service after the effective date of this AD, unless already accomplished, inspect the rivet attachment of the two weights (P/N 28-21250-16) to the bottom rudder balance weight assembly (P/N 28-21250-14). There are five 1/8-inch rivets per weight, a total of ten for the entire assembly. If any looseness or failure of the rivets is found, replace all rivets with bolts in accordance with (c). (c) Within the next 250 hours' time in service after theeffective date of this AD, replace the ten 1/8-inch rivets referred to in (b) with AN 509-10R-30 bolts, AN 960-10 washers and NAS 679A3W lock nuts. This requires countersinking the aft face of the P/N 28-21250-14 assembly to accommodate the bolt heads. When this modification has been accomplished, the inspection in (a) may be discontinued. (Canadair Service Information Circular 262-CL44D4 covers this subject.) This directive effective February 6, 1963.
2005-19-11: The FAA is adopting a new airworthiness directive (AD) for certain Lycoming Engines (formerly Textron Lycoming) AEIO-360, IO-360, O-360, LIO-360, LO-360, AEIO-540, IO-540, O-540, and TIO-540 series reciprocating engines rated at 300 horsepower (HP) or lower. This AD requires replacing certain crankshafts. This AD results from reports of 12 crankshaft failures in Lycoming 360 and 540 series engines rated at 300 HP or lower. We are issuing this AD to prevent failure of the crankshaft, which could result in total engine power loss, in-flight engine failure, and possible loss of the aircraft.
2016-08-01: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 7X airplanes. This AD was prompted by reports of multiple cases of ram air turbine (RAT) blade damage. This AD requires deployment of the RAT, replacement of the RAT placard with a new RAT placard, and re-identification of the RAT. We are issuing this AD to prevent blade damage to the RAT, which could prevent RAT deployment in flight during an emergency, possibly resulting in reduced control of the airplane.
98-04-16: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. This AD requires inspecting the aileron tie-rod jam nuts for looseness, tightening any loose jam nuts, and installing a locking sleeve on both ends of the aileron tie-rod in the chain-drive of the aileron system. The AD results from an incident where the aileron tie-rod jam nuts on the chain-drive of the aileron system became loose. This caused a differential of aileron control between the pilot's control wheel and the co-pilot's control wheel. The actions specified by this AD are intended to prevent such aileron control differential caused by the aileron tie-rod jam nuts becoming loose, which could result in loss of aileron control and consequent loss of control of the airplane.
83-07-22 R1: 83-07-22 R1 PARTENAVIA COSTRUZIONI AERONAUTICHE S.p.A.: Amendment 39- 4624 as amended by Amendment 39-4700. Applies to Model P-68B, P-68C, and P-68C-TC airplanes (all S/Ns up to S/N 255 excluding S/Ns 220, 224, 227, 228, 234, 235, 236, 239, 249, 251, 252, 253, and 254) certificated in any category. Compliance: Required within the next 100 hours time-in-service, unless already accomplished. To prevent unintentional return of flaps to the zero degree position, accomplish the following: (a) Replace the flap selector switch with a new type switch, P/N 7.2345D-1 (MS25201-5) as prescribed in Service Bulletin No. 55 dated September 2, 1982. (b) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location where this AD can be accomplished. (c) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy,1000 Brussels, Belgium. Amendment 39-4624 became effective on April 14, 1983. This Amendment 39-4700 becomes effective August 9, 1983.
2005-19-07: The FAA adopts a new airworthiness directive (AD) for certain Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD requires you to replace the rudder pedal arm assemblies used in the rudder control system with parts of improved design. This AD results from reports of cracks found on the rudder pedal arm assemblies. We are issuing this AD to prevent failure of the rudder pedal arm assemblies caused by fatigue cracks. This failure could lead to loss of rudder control, loss of nose gear steering, and loss of toe brakes on the side on which the failure occurs.
98-04-26: This amendment adopts a new airworthiness directive (AD) that applies to The New Piper Aircraft Corporation Models PA-46-310P and PA-46-350P airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to prevent minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
98-04-01: This amendment adopts a new airworthiness directive (AD) that applies to certain EXTRA Flugzeugbau GmbH Model EA-300/S airplanes. This AD requires modifying the canopy latches or replacing the canopy latches with parts of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to prevent failure of the canopy while the airplane is in flight because of cracked canopy latches, which could result in loss of the canopy and possible loss of control of the airplane.
60-03-01: 60-03-01\tBOEING: Amdt. 87 Part 507 Federal Register January 26, 1960. Applies to all Model 707 series aircraft. \n\n\tDue to recent failures of the wing foreflaps, the following must be accomplished at times indicated: \n\n\t(a)\tConduct daily inspection of the original type outboard foreflap, P/N's 65-7360-3007 and 65-7360-3008, on outboard mainflap as follows: \n\n\t\t(1)\tConduct detail visual inspection of foreflaps for any evidence of cracking. \n\n\t\t(2)\tBy use of borescope or equivalent, inspect interior web, flanges and cutouts on both the inboard and outboard end ribs for cracks or other damage. \n\n\t\t(3)\tBy means of dye check or equivalent, examine skin areas at ends of reinforcement plate on upper surface. \n\n\t(b)\tWhen the original type outboard foreflap on each outboard mainflap has been replaced with the redesigned type, P/N's 65-7360-3023 and 65-7360-3024, the daily inspection, (a) above, may be discontinued. However, the redesigned foreflap must then be inspected at intervals not to exceed 65 hours' time in service as prescribed in (a)(1) and (a)(2) above. \n\n\t(c)\tAny outboard foreflap showing evidence of cracking or other damage must be replaced or repaired in accordance with FAA approved manufacturer's instructions prior to next flight. \n\n\t(d)\tThe special inspections of the outboard foreflap, P/N's 65-7360-3023 and 65-7360- 3024, prescribed in (b) above may be discontinued when an inertia damper P/N's 69-11124-1 (left wing) and 69-11124-2 (right wing) has been installed on the foreflaps.\n \n\t(Boeing Service Bulletins No. 456 (R-2) dated November 18, 1959, and No. 566 dated August 26, 1959, cover criteria on the same subject.) \n\n\tThis supersedes AD 59-25-01.
98-04-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and C-9 (military) series airplanes, that currently requires eddy current or dye penetrant inspection for cracks in the upper fuselage skin in the area of the aft pressure bulkhead tee. This amendment requires new improved repetitive inspections and follow-on actions, and expands the applicability of the existing AD to include additional airplanes. This amendment is prompted by additional reports of fatigue cracking and improperly seated attachments in the upper fuselage skin in the area of the aft pressure bulkhead tee. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage and consequent reduced structural integrity of the airplane.
2016-08-12: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 787-8 and 787-9 airplanes powered by General Electric (GE) GEnx-1B engines. This AD requires revising the airplane flight manual (AFM) to provide the flight crew a revised fan ice removal procedure and a new associated mandatory flight crew briefing to reduce the likelihood of engine damage due to fan ice shedding. This AD also removes certain dispatch relief. For airplanes with certain engines, this AD also requires reworking or replacing at least one engine. This AD was prompted by a recent engine fan blade rub event that caused an in-flight non-restartable power loss. We are issuing this AD to prevent susceptibility to heavy fan blade rubs, which could result in engine damage and a possible in-flight non-restartable power loss of one or both engines.
98-04-04: This amendment adopts a new airworthiness directive (AD) that applies to certain SOCATA - Groupe AEROSPATIALE (Socata) Model TBM 700 airplanes. This AD requires replacing the starter generator mounting adapter with a part of improved design. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for France. The actions specified by this AD are intended to prevent loss of the starter generator caused by failure of the starter generator mounting adapter, which could result in loss of electrical power.
80-17-14: 80-17-14 BENDIX: Amendment 39-3886. Applies to Bendix D-2000 and D-2200 series magnetos installed on 4, 6, or 8 cylinder reciprocating engines. To preclude the loss of ignition, accomplish the instructions shown in the following sections of Bendix Service Bulletin No. 605A or an FAA-approved equivalent, within the next 50 hours' time in service after the effective date of this AD unless previously accomplished. a. Service Bulletin Section 2, Housing Distortion Check: 1. For red nameplate magnetos with serial numbers above 25000. 2. For any magneto, regardless of serial number, which has operated with the four center cover screws installed after compliance with AD 79-18-06. b. Service Bulletin Section 4, Installation of Cover Sealing Kit and Cover Decals. c. Service Bulletin Section 5, Identification After Compliance. d. Make an engine log book entry of compliance, including magneto serial number. Equivalent inspections and procedures mustbe approved by the Chief of the Engineering and Manufacturing Branch, AEA-210, Federal Aviation Administration (FAA) Eastern Region. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this Airworthiness Directive can be accomplished. This amendment is effective August 21, 1980.
62-22-03: 62-22-03 VICKERS: Amdt. 491 Part 507 Federal Register October 5, 1962. Applies to All Viscount 700 Series Aircraft. Compliance required as indicated. As a result of wing flap attachment difficulties the following is required for both flap assemblies: (a) (1) Replace bolts P/N's 72403-2445, 70103-2645, and 70103-2639, at flap support bracket units Nos. 2 and 3 respectively, right and left side with new bolts every 1,500 landings. (2) Replace bolts P/N's 70003-2359 and 70107-467, at flap support bracket units Nos. 1 and 4 respectively, right and left side with new bolts every 2,500 landings. (3) When Modification D.2175 is incorporated and provided the bolts referred to in paragraphs (a)(1) and (a)(2) are replaced with new bolts at the same time, the life of these new bolts is extended as specified in the overhaul schedule listed below: Part Number 72403-2445 - Retirement time 4,500 landings Part Number 70103-2645 - Retirement time 4,500 landings PartNumber 70103-2639 - Retirement time 4,500 landings Part Number 70003-2359 - Retirement time 7,500 landings Part Number 70107-467 - Retirement time 7,500 landings (b) Flap beam (supporting bracket) attachment fitting at wing trailing edge false spar member inspection. (1) Within the next 135 hours' time in service after the effective date of this AD and each 135 hours' time in service thereafter, visually inspect for cracks all four lower flap support attachment fittings aft of the wing trailing edge member (false spar) on the right and left sides. The initial inspection is not required if these fittings were thoroughly examined at the time of bolt replacement of paragraph (a). (2) Within the next 385 hours' time in service after the effective date of this AD and each 1,080 hours' time in service thereafter, visually inspect for cracks all the flap support attachment fittings forward of the trailing edge member (false spar), top and bottom, right and left sides at flap positions 2 and 3. (3) Within the next 385 hours' time in service after the effective date of this AD and each 385 hours' time in service thereafter, visually inspect for cracks all top beam attachment fittings aft of the trailing edge member (false spar) on the right and left sides. (c) Replace cracked fittings. (d) Incorporated Vickers Modification D.2175 within the next 400 hours' time in service after the effective date of this AD on aircraft exceeding 3,000 landings, or within 400 hours' time in service upon the accumulation of 3,000 landings on aircraft not exceeding 3,000 landings on the effective date of this AD. Upon incorporation of this modification, the inspections called for in (b)(1), (b)(2), and (b)(3) may be discontinued. (Vickers Viscount 700 Series PTL No. 151, Issue 4 covers this subject.) This supersedes AD 57-07-03. This directive effective November 6, 1962.
2005-19-02: The FAA is adopting a new airworthiness directive (AD) for all EMBRAER Model EMB-110P1 and EMB-110P2 airplanes. This AD requires repetitive inspections for corrosion or cracking of the rotating cylinder assembly in the nose landing gear (NLG), and related investigative/corrective actions if necessary. This AD also requires the eventual replacement of the rotating cylinder assembly with a new part, which terminates the need for the repetitive inspections. This AD results from reports of corrosion on the NLG rotating cylinder assembly. We are issuing this AD to prevent cracks from emanating from corrosion pits in the NLG rotating cylinder assembly, which could result in failure of the NLG.
98-03-18: This amendment supersedes an existing airworthiness directive (AD), applicable to all Fokker Model F28 Mark 0100 and 0070 series airplanes, that currently requires revising the Airplane Flight Manual (AFM) to include information that will enable the flightcrew to identify failures of the emergency direct current (DC)/alternating current (AC) bus power supply and to take appropriate corrective actions. This amendment requires a new terminating modification for the existing AFM revisions. This amendment also requires a new AFM revision to inform the flightcrew that, under certain conditions, an "EMER DC BUS" warning on the multi-function display unit (MFDU) will occur, and to take appropriate corrective actions. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failures of the emergency DC/AC bus power supply, which could reduce theability of the flightcrew to control the airplane.
98-03-13: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA and SD3 SHERPA series airplanes, that requires removing the aluminum alloy oxygen pipe assembly and replacing it with a stainless steel assembly. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent aluminum oxygen tubing from bursting and releasing a high-pressure oxygen flow into the passenger cabin, which could result in a fire hazard during flight.
98-03-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737, 747, 757, and 767 series airplanes, that currently requires a one-time operational test of the pilots' seat locks and the seat tracks to ensure that the seats lock in position and the seat tracks are aligned correctly; and re-alignment of the seat tracks, if necessary. This amendment revises the applicability of the existing AD. The actions specified in this AD are intended to prevent uncommanded movement of the pilots' seats during acceleration and take-off of the airplane, and consequent reduced controllability of the airplane.
60-05-01: 60-05-01 FAIRCHILD: Amdt. 109 Part 507 Federal Register March 2, 1960. Applies to Models F-27, F-27A, and F-27B, Serial Numbers 1 to 65 inclusive. Compliance required by April 15, 1960. As a result of investigation of loose rivets in the rudder torque tube assembly, the following shall be accomplished: Replace all "Olympic" rivets "Huck" lockbolts, P/N BL-8-3, in rudder torque tube assembly, P/N 727413-1, where the ends, P/N 27-727414-3 and 27-727415-3, are secured to the tube, P/N 27-727424-3. (Fairchild Service Bulletin No. 27-15, revised September 8, 1959, covers this subject.)
2017-01-04: We are adopting a new airworthiness directive (AD) for certain Fokker Services B.V. Model F28 Mark 0100 airplanes. This AD was prompted by an analysis which determined that, for certain areas of the fuselage, the current threshold of an Airworthiness Limitations Section inspection is insufficient to detect early crack development. This AD requires one time high and low frequency eddy current inspections of the affected fuselage skin for cracks, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
2016-21-07: We are superseding airworthiness directive (AD) 2015-12-04 for all Honeywell International Inc. (Honeywell) TPE331-1, -2, -2UA, -3U, - 3UW, -5, -5A, -5AB, -5B, -6, -6A, -10, -10AV, -10GP, -10GT, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, -10UR, -11U, -12JR, -12UA, - 12UAR, and -12UHR turboprop engines with certain Woodward fuel control unit (FCU) assemblies, installed. AD 2015-12-04 required initial and repetitive dimensional inspections of the affected fuel control drives and insertion of certain airplane operating procedures into the applicable flight manuals. This AD corrects the compliance requirements and relaxes the inspection interval. This AD was prompted by a request to change compliance time from 50 hours to 100 hours for affected fuel controls. We are [[Page 73021]] issuing this AD to prevent failure of the fuel control drive, damage to the engine, and damage to the airplane.