Results
79-13-08: 79-13-08 AIRBORNE MANUFACTURING COMPANY: Amendment 39-3507. Applies to the below listed part number Dry Air Pumps installed on piston engine aircraft certificated in all categories. AIRBORNE PART NUMBER SERIAL NUMBERS 211 CC 5E9318 thru 5E9347 5E9407 thru 5E11419 211 CC-9 5E616 thru 5E715 211 CC TR 5E1264 thru 5E1406 212 CW 5E3403 thru 5E4197 5E9129E thru 5E9131E 212 CW-6 5E9 thru 5E25 242 CW-4 5E8 thru 5E11 441 CC 5E332 thru 5E401 5E450 thru 5E483 441 CC-7 5E911 thru 5E981 441 CC-9 5E75 thru 5E80 441 CC-11 5E4 441 CC-13 5E7 thru 5E12 441 CC-17 5E106 thru 5E116 442 CW 5E926 thru 5E1023 442 CW-4 5E137 thru 5E149 442 CW-6 5E765 thru 5E785 442 CW-8 5E114 442 CW-12 5E431 thru 5E435 These pumps were not available for installation before May 15, 1979, therefore, dry air pumps installed previous to that date are exempt from this AD. Compliance is required prior to next flight. To prevent catastrophic failure of the pump and subsequent loss of the vacuum system remove above listed dry air pumps from service and replace with an airworthy pump of the same part number. An airworthy pump is one which has a serial number not listed above or if listed above also has an "A" or "2" ink stamped by the manufacturer with black ink on the periphery of the body near the mounting flange. The aircraft may be flown under day VFR conditions in accordance with FAR 21.197 to a base where the corrective action can be performed. Additional information concerning disposition of the affected pumps is contained in Airborne Manufacturing Company, Aviation Products Group, Service Letter Number 22A, dated June 5, 1979. This amendment becomes effective upon publication in the Federal Register, as to all persons except those to whom it was made immediately effective by the airmail letter dated June 7, 1979, which contained this amendment.
2005-20-28: The FAA is adopting a new airworthiness directive (AD) for certain Airbus airplane models, as specified above. This AD requires modifying the floor proximity emergency escape path marking system. This AD results from information that the existing system design for interconnection of the emergency power supply units of the floor proximity emergency escape path marking system does not provide adequate floor path lighting and marking for safe evacuation of the airplane in the event of an emergency. We are issuing this AD to prevent inadequate lighting and marking of the escape path, which could delay or impede the flightcrew and passengers when exiting the airplane during an emergency landing.
98-12-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires modifying the low pitch stop switch support. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent low pitch stop switch support displacement, which could result in an improper cockpit indication that the propeller is in the Beta range and cause loss of control of the airplane.
98-12-09: This amendment adopts a new airworthiness directive (AD), applicable to AlliedSignal Inc. Model TPE331 series turboprop engines, that requires removal of suspect fuel manifold assemblies and replacement with serviceable assemblies. This amendment is prompted by an FAA investigation into Hoses Unlimited's repairs of TPE331 fuel manifolds, which were not approved by the FAA. The actions specified by this AD are intended to prevent fuel leakage at the fuel manifold fittings, resulting in fuel spraying on hot turbine components, which could result in an engine fire.
78-23-05: 78-23-05 CANADAIR: Amendment 39-3338. Applies to CL-44D4 and CL-44J airplanes, certificated in all categories. To preclude loss of elevator travel due to spline wear; (a) Within the next 100 hours in service after the effective date of this airworthiness directive, unless already accomplished within the last 900 hours in service, and thereafter at intervals not to exceed 1000 hours in service, accomplish the following: (1) Visually inspect each elevator resilient stop mechanism at spanwise stations 43 and 178 for wear, in accordance with Inspection Data paragraph of Canadair Service Information Circular (SIC) Number 406-CL44, dated May 17, 1977, or equivalent. (2) Prior to next flight, repair or replace worn parts with parts of the same part number and install in accordance with instructions outlined in Chapter 55-20-2 of the Canadair CL-44 Overhaul Manual, dated June 19, 1964, or equivalent. (b) Equivalent inspections and repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (c) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the compliance times specified in this AD. This amendment is effective November 10, 1978.
2005-20-21: The FAA is adopting a new airworthiness directive (AD) for certain Fokker Model F27 Mark 050 airplanes. This AD requires repetitive visual checks for oil leaks of both engines between the spinner and the engine cowling, and directly behind the heated intake lip of the engine; repetitive inspections for oil leaks at the feathering pump on both engines; and corrective actions if necessary. This AD results from reports of oil leakage at the engine feathering pump. We are issuing this AD to prevent oil loss from the feathering pump, which could cause the engine to shut down in flight.
98-12-04: This amendment adopts a new airworthiness directive (AD) that applies to all Glaser-Dirks Flugzeugbau GmbH (Glaser-Dirks) Model DG-500M gliders. This AD requires installing a rudder gap seal and modifying the cooling liquid reservoir mount. 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 rudder vibrations caused by flow separation at the rudder gap, which could result in flutter with consequent loss of rudder control.
63-06-03: 63-06-03 GENERAL DYNAMICS/CONVAIR: Amdt. 545 Part 507 Federal Register March 20, 1963. Applies to All Models 340 and 440 Series Aircraft Equipped With a Bendix Redbank Type 35E05 Fault Detection Panel. Compliance required within the next 300 hours' time in service following the effective date of this AD, unless already accomplished. To prevent the loss of electrical power, modify the type 35E05 fault detection panel by installing a blocking rectifier (G.E. IN-93 or FAA approved equivalent). Solder the negative lead to lug No. 3 of the locating relay and the positive lead to terminal No. P on the terminal board. (Convair Airgram No. 200 dated September 24, 1956, and Bendix Redbank Service Bulletin No. R-47 pertains to this same modification.) This directive effective March 20, 1963.
82-23-06: 82-23-06 FAIRCHILD SWEARINGEN: Amendment 39-4493. Applies to Models SA 226-T(B) (S/N T(B) 276, T(B) 292 through T(B) 397); SA 226-T (S/N T201 through T275 and T277 through T291); SA 226-AT (S/N AT001 through AT074); SA 226-TC (S/N TC201 through TC396) airplanes certificated in any category. COMPLIANCE: Required within the next 50 hours time-in-service unless already accomplished. To prevent the main landing gear doors from shifting and locking the gear in the up position, accomplish the following: (a) Inspect, check, and modify the main landing gear door installation in accordance with Accomplishment Instructions IIA through IIL of Fairchild Swearingen Service Bulletin SB 32-026 dated October 16, 1980, as supplemented by the instructions below. (1) When replacing the bushings and refitting the doors for final assembly, assure that the bushings are properly lubricated (do not use thin-film, spray-on liquids which will wash out the grease from the Oilite bushings; use a thick, permanent lubricant such as Lubriplate). (2) Observe standard torque for AN3 bolts. (3) Assure that the door hinge bolts clamp completely and the doors move freely. (4) Remove stripped nutplates and replace them with a castellated nut and cotter pin. Instructions for accomplishing this may be obtained from Fairchild Swearingen Corporation. Use of the drilled bolt and safety wire procedures specified in paragraphs IIG and IIJ of Fairchild Swearingen Service Bulletin SB 32-026 is not required if a castellated nut and cotter pin are used. (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 when approved by the Manager, Aircraft Certification Division, ASW-100, Southwest Regional Office, FAA, Fort Worth, Texas 76101; telephone (817) 624-4911, extension 511. This amendment becomes effective on November 15, 1982.
2005-20-15: The FAA is adopting a new airworthiness directive (AD) for certain McDonnell Douglas transport category airplanes. This AD requires an inspection of the rudder pedal torque tube assembly for cracking; an inspection of the torque tube assembly to determine the thickness of the torque tube wall, if necessary; and replacing the rudder torque tube with a new or serviceable rudder torque tube, if necessary. This AD results from a report of a broken rudder pedal torque tube. We are issuing this AD to prevent failure of a rudder pedal torque tube, which could result in loss of rudder control and nose wheel steering controlled by the rudder pedal, and consequent reduced controllability of the airplane.