Results
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.