Results
86-23-51: 86-23-51 BOEING VERTOL: Amendment 39-5659. Applies to Boeing Vertol Model 234 series helicopters certificated in any category, equipped with forward rotor transmission P/N's 234D1200-2, -3, -4, -5, and -6 and/or aft rotor transmission P/N's 234D2200-3, -4, and -5. Compliance is required as indicated, unless already accomplished. To prevent failure of the spiral bevel ring gear/sun gear bolted joint, accomplish the following before further flight. (a) For both forward and aft transmissions, remove all spiral bevel ring gears, P/N's 114D1244-5 and -6 and 114D2254-5 and -6; first stage sun gears, P/N's 234D1243-1 and -2 and 234D2250-1 and -2; and spacer shim, P/N's 114D2257-1 and -2, with more than zero hours time in service. Spiral bevel ring gears, P/N's 114D1244-6 and 114D2254-6; first stage sun gears, P/N's 234D1243-2 and 234D2250-2; and spacer shim, P/N 114D2257-2, are not eligible for further service. (b) Install the following parts, which must be new, except for the first stage sun gear, (item (b)(2) below), which must be serviceable: (1) Spiral bevel ring gear, P/N 114D1244-5 or 114D2254-5; (2) First stage sun gear, P/N 234D1243-1 or 234D2250-1; (3) Spacer shim, P/N 114D2257-1; and (4) Associated hardware as follows: (i) Bolt, P/N BACB30MT6T12; (ii) Washer, P/N BACW10BP6P; and (iii) Nut, P/N BACN10TW6. (c) An alternate method of compliance which provides an equivalent level of safety with this AD may be used when approved by the Manager, New York Aircraft Certification Office, 181 South Franklin Avenue, Rm. 202, Valley Stream, NY 11581. This amendment, 39-5659, becomes effective July 20, 1987, as to all persons except those persons to whom it was made immediately effective by individual telegrams issued November 14, 1986, which contained this amendment.
60-07-06: 60-07-06 MARTIN: Amdt. 118 Part 507 Federal Register March 25, 1960. Applies to All Model 404 Aircraft. Compliance required as indicated. Investigation of a recent Model 404 wheels up landing disclosed that the landing gear lock linkage and lock plunger malfunctioned. Inspection of the jury strut revealed that when the lock plunger was pulled back to normal travel limits in operating the "free fall" actuating mechanism to "full travel", the plunger would periodically jam in the retracted position and consequently flare out in the form of a knife edge. Also, cutting action was evident in the forward bushings (in the plunger cylinder) in an area coincident with the two flared edges. To prevent further lock plunger malfunctioning, the following must be accomplished: (a) Replace lock plunger P/N 404-4088121-3 with new lock plunger P/N 404- 4900121-5 on each main landing gear by July 31, 1960. (b) At each 320 hours' time in service commencing not later than May15, 1960, visually inspect main and nose gear lock plungers for a spalling or flaring condition. Check the lock plunger for free operation. The plunger should be free from dirt, dust, moisture, ice, etc. If spalling or flaring exists, the lock plunger must be chamfered (rounded out) at the corners of the plunger for the full length of the flat area. (Martin Service Bulletin No. 404-260 dated October 30, 1952, partially covers this subject.)
2019-21-09: The FAA is adopting a new airworthiness directive (AD) for certain Aviointeriors S.p.A. (Aviointeriors) Centaurus passenger seats with a specific life vest pouch assembly installed. This AD was prompted by reports of life vest pouches that were installed incorrectly on certain seats. This AD requires inspection of the life vest pouch assembly and, depending on the results of the inspection, replacement of the life vest pouch assembly. The FAA is issuing this AD to address the unsafe condition on these products.
95-22-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Canadair Model CL-215-1A10 and CL-215-6B11 series airplanes. This action requires inspections to detect cracking of main landing gear (MLG) axles that have been reworked by chromium plating, and replacement of cracked axles. This amendment is prompted by reports of fatigue cracking found on several MLG wheel axes that had been chromium-plated during rework. The actions specified in this AD are intended to prevent such cracking, which can result in failure of the axle, separation of the wheel from the aircraft, and consequent reduced controllability of the airplane during takeoff or landing.
2007-16-12: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 757-200 and -300 series airplanes. This AD requires changes to existing wiring; installation of new circuit breakers, relays, relay connectors, and wiring; and replacement of certain circuit breakers with higher-rated circuit breakers. For certain airplanes, this AD also requires modification of wiring of the control module assembly for the electrical systems. This AD results from an in-flight entertainment (IFE) systems review. We are issuing this AD to ensure that the flightcrew is able to turn off electrical power to the IFE system and other non-essential electrical systems through utility bus switches in the flight compartment. The flightcrew's inability to turn off power to the IFE system and other non-essential electrical systems during a non-normal or emergency situation could result in the inability to control smoke or fumes in the airplane flight deck or cabin.
2007-15-06: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 airplanes. This AD requires revising the Airworthiness Limitations section of the Instructions for Continued Airworthiness to incorporate new limitations for fuel tank systems. This AD results from fuel system reviews conducted by the manufacturer. We are issuing this AD to prevent the potential of ignition sources inside fuel tanks, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2019-20-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A318 and A319 series airplanes, Model A320- 211, -212, -214, -216, -231, -232, and -233 airplanes, and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by a report that cracks were detected on frame (FR) 16 and FR 20 web holes and passenger door intercostal fitting holes at the door stop fitting locations. This AD requires repetitive rototest inspections of the holes at the door stop fittings for any cracking, and corrective actions if necessary, as specified in a European Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
99-17-12: This amendment adopts a new airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146 and Model Avro 146-RJ series airplanes, that requires a one-time measurement to determine the thickness of the outer links of the side stays of the main landing gear (MLG), and corrective actions, if necessary. This amendment also provides for replacement of a thin outer link with a new or serviceable part in lieu of certain follow-on inspections. 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 cracking of the outer links of the side stays of the MLG, which could result in failure of a side stay, and consequent collapse of the landing gear.
99-07-16: This amendment adopts a new airworthiness directive (AD), applicable to Sikorsky Aircraft-manufactured Model CH-54A helicopters, that requires an initial and recurring inspections and rework or replacement, if necessary, of the second stage lower planetary plate (plate). This amendment is prompted by cracked plates that have been found during overhaul and inspections. The actions specified by this AD are intended to prevent failure of the plate due to fatigue cracking, which could result in failure of the main gearbox, failure of the drive system, and subsequent loss of control of the helicopter.
79-10-05: 79-10-05 BOEING: Amendment 38-3463. Applies to all Model 727 series airplanes, certificated in all categories, with outboard trailing edge foreflap sequence carriage sliders made from polyimide plastic. Compliance required as indicated. \n\tA.\tWithin the next 200 landings from the effective date of this AD, and thereafter at intervals not to exceed 200 landings inspect the sliders for cracks or missing pieces in accordance with Boeing Alert Service Bulletin No. 727-57-A147, or later FAA approved revisions, or an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tB.\tCracked sliders are to be replaced prior to further flight, except that if a slider is cracked or missing pieces exist at only one attach bolt hole location, as noted in Boeing Alert Service Bulletin No. 727-57-A147, the slider may remain in service but must be inspected at intervals not to exceed 50 landings and must be replaced within 200 flights from detection of the initial cracking. \n\tC.\tTerminating action of this AD consists of replacement of outboard trailing edge foreflap sequence carriage sliders with Boeing supplied Beryllium Copper sliders or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tD.\tAirplanes may be flown to a maintenance base for replacement in accordance with FAR 21.197. \n\tThe manufacturer's specification and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer, may obtain copies upon request to Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective May 18, 1979.