Results
2003-04-12: This amendment adopts a new airworthiness directive (AD) for the specified Bell Helicopter Textron Canada (Bell) model helicopters that requires modifying the auxiliary fin assemblies and revising the Limitations section of the Rotorcraft Flight Manual (RFM) to reduce the never-exceed speed (Vne) for a tail rotor pedal stop failure. This amendment is prompted by several incidents of main rotor blades contacting the top of the fin that have resulted in an upper tuning weight (weight) becoming loose. The actions specified by this AD are intended to prevent a main rotor blade from striking an auxiliary fin, loss of a tuning weight, impact with a tail or main rotor blade, and subsequent loss of control of the helicopter.
2003-04-22: This amendment adopts a new airworthiness directive (AD), that is applicable to Hartzell Propeller Inc. model HD-E6C-3B/E13890K propellers with certain serial numbers of model D-1199-2 propeller control units (PCU's) installed. This amendment requires initial and repetitive inspections for below-limit propeller flight idle blade angles, and, as a terminating action, removal of the affected PCU's from service and performance of a complete Major Periodic Inspection (overhaul) when the applicable time-since-new or time-since-overhaul limit is reached, or when any flight idle blade angle is below limits. This amendment is prompted by a review by Hartzell Propeller Inc. of the model D-1199-2 PCU overhaul procedures, that revealed several dimensional checks and a nondestructive evaluation were not performed on certain serial number PCU's during a Major Periodic Inspection (overhaul). The overhaul procedures are required to comply with the Airworthiness Limitation PCU Major PeriodicInspection (overhaul) directive. The actions specified by this AD are intended to prevent below-limit flight idle propeller blade angles that, if not corrected, could result in degraded aircraft performance and control.
98-06-11: This amendment adopts a new airworthiness directive (AD), applicable to certain de Havilland Model DHC-8-100 series airplanes, that requires a one-time visual inspection to determine the presence of block seals on the upper portions of the cabin/baggage compartment bulkheads, and installation of a new or serviceable block seal for any missing block seal. 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 smoke contamination of the passenger and crew cabins, in the event of fire or smoke in the baggage compartment, due to a direct smoke path between the baggage compartment and the cabins.
55-17-01: 55-17-01 LOCKHEED: Applies to All Models 49, 149, 649, 749, and 1049 Airplanes. Compliance required by December 1, 1955, unless already accomplished. A recent failure of wing flap torque tube assembly, P/N 326605-3, on a Model 1049C is attributed to a defective bolt, P/N AN 23-19. Initial overtorque of the bolt is suspected as the cause of failure of the bolt. It is therefore necessary that all Constellation and Super Constellation airplanes be inspected to ascertain proper installation of bolts, including bolt torque, on all wing flap torque tubes. Proper torque value for the AN 23-19 bolts is 10 to 20 inch-pounds. Nut torque must be checked with a torque wrench and all overtorqued bolts replaced. If necessary, the next size longer bolt (P/N AN23-20) may be used to facilitate installation within proper torque tolerances. Washers may be used as required, but not to exceed two under the head or two under the nut, to prevent the nut from bottoming on the shank.
98-07-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and -300 series airplanes, that requires a one-time inspection for worn or broken wire bundles in the ceiling above the main passenger door and repair, if necessary; and relocation of the wire bundles to prevent chafing. This amendment is prompted by a report indicating that the opening of the main passenger door caused the door liner and a ceiling panel to chafe and ultimately break wires installed in this area. The actions specified by this AD are intended to prevent these wires from becoming worn or breaking, which could lead to the failure of several systems, such as the fuel shutoff valves, and may contribute to the inability of the flight crew to stop the flow of fuel to the engines in the event of an engine fire.
2018-03-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318 series airplanes; Model A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321- 111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This AD was prompted by reports of fatigue damage in the structure for the door stop fittings on certain fuselage frames (FR). This AD requires repetitive rototest inspections for cracking of the fastener holes in certain door stop fittings, and repair if necessary. We are issuing this AD to address the unsafe condition on these products.
55-22-02: 55-22-02 ERCO: Applies to 415-C, -CD and -D Aircraft Serial Numbers 113 Through 2468 for Fuselage Tank Replacement; Serial Numbers 113 Through 2622 For Wing Tank Replacements. Inspection required each 25 hours; replacement at time leakage discovered. Unless the terneplate fuselage fuel tank has been replaced with a stainless steel tank and the terneplate wing fuel tanks replaced with aluminum alloy or stainless steel tanks, the tanks should be inspected frequently for signs of leakage at intervals not greater than 25 hours. If tank leakage is observed, the tank should be replaced with one of stainless steel or aluminum alloy, as required, before the next flight. Erco Service Department Bulletins No. 10 and No. 10A and Memorandums No. 31 and 43 pertain to the inspection and replacement of these tanks. This supersedes AD 47-50-10.
83-07-19: 83-07-19 WYTWORNIA SPRZETU KOMUNIKACYJNEGO PZL-MIELEC: Amendment 39-4621. Applies to Model PZL M18 (Serial Numbers 1Z005-11 through 1Z005-14) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service after effective date of this AD, unless already accomplished. To prevent loss of primary flight control about the airplane roll axis, accomplish the following: a) Replace the connecting segment of the aileron push rods with Part No. 3-26x1- 430 ZN-72/L-381-307 as prescribed in Mandatory Bulletin No. I/012/81 dated 4/81. 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.
98-07-11: This amendment adopts a new airworthiness directive (AD) that is applicable to GKN Westland Helicopters Limited (Westland) WG-30 series 100 and 100-60 helicopters. This action requires an initial visual inspection and replacement, if necessary, of all main rotor head tie-bars. Thereafter, this AD requires, at intervals not to exceed 220 hours time-in-service (TIS), replacing each main rotor head tie-bar (tie-bar) with an airworthy tie-bar. This amendment is prompted by an accident on a similar model military helicopter in which a tie-bar failed; it is suspected that the military helicopter involved in the accident exceeded the power-off transient rotor speed limitation. This condition, if not corrected, could result in failure of a tie-bar, loss of a main rotor blade, and subsequent loss of control of the helicopter.
83-03-02 R1: 83-03-02 R1 ALLISON GAS TURBINE OPERATIONS/DETROIT DIESEL ALLISON (ALLISON): Amendment 39-4560 as amended by Amendment 39-4814. Applies to all Model 250-C20, -C20B, -C20C (T63- A720), -C20F, -B17, -B17B, -B17C, and -B17D engines equipped with the following slotted third stage turbine wheels: PART NO. TYPE OF SHROUD PART NO. TYPE OF SHROUD 6887113 Full slot 6898823 Crimped full slot 6888633 Full slot 6899364 Crimped full slot 6896863 Crimped full slot 6899406 Crimped center slot 6898551 Center slot 6899415 Crimped center slot 6898567 Center slot 6899416 Crimped center slot 6898733 Center slot 6899417 Crimped center slot 6898743 Center slot 6899418 Crimped center slot 6898753 Center slot 6899419 Crimped center slot 6898763 Center slot Accomplish the following to prevent possible engine power loss resulting from partial blade and/or shroud separation of slotted third stage turbine wheels: 1. Compliance required,as indicated, unless already accomplished: Remove from service and replace affected turbine wheels per the accomplishment instructions provided in Allison Commercial Engine Alert Bulletin CEB-A-1174/1146, Revision 3 dated January 26, 1984, or FAA approved equivalent, in accordance with the following schedule: Wheel Time Since New (TSN) - Hours Remove 1650 or more Within the next 100 hours time in service. 1000 or more and less than 1650 Within the next 400 hours time in service, or prior to exceeding 1750 hours TSN, whichever comes first. More than 500 and less than 1000 Within the next 600 hours time in service, or prior to exceeding 1500 hours TSN, whichever comes first. 500 or less Within the next 850 hours time in service, or prior to exceeding 1100 hours TSN, whichever comes first. 2. Compliance required not later than August 12, 1983, unless already accomplished: a. Placards, markings, or flight manual changes shall be provided to flight crews to avoid sustained operation of all affected engines between 90 and 98 percent N2, except during transients, while maintaining safe flight practices. This restriction also applies to autorotation practice and engine idle during engine-out simulation on multiengine aircraft. b. During all ground operation of affected turbine wheels installed in 250-C20, -C20B, C20C (T63-A720 engines, the engine N1 speed must be maintained at ground idle, except during transient operations, when performing required operational checks, or in high or gusty wind conditions, or where safety would be adversely affected. Placards, markings, or flight manual changes shall be used to advise flight crews of the ground operating restriction. c. During all ground operation of affected turbine wheels installed in 250-B17, -B17B, -B17C engines, the engine N2 speed must be maintained below 90 percent N2 r.p.m., except during transient operation, when performing required operational checks or in high or gusty wind conditions, or where safety would be adversely affected. Placards, markings, or flight manual changes shall be used to advise flight crews of the ground operating restriction. Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, Central Region. Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate aircraft to a base where compliance with this AD can be accomplished. The manufacturer's specifications 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 Allison Gas Turbine Operations, General Motors Corporation, Indianapolis, Indiana 46206-0420. These documents may also be examined at the New EnglandRegional Office, 12 New England Executive Park, Burlington, Massachusetts 01803. A historical file on this AD is maintained by the FAA at the New England Regional Office. This AD supersedes Amendment 39-3011, 42 FR 43969, AD 77-18-03. Amendment 39-4560 became effective June 13, 1983. This Amendment 39-4814 becomes effective February 28, 1984.