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2003-21-01: The FAA supersedes Airworthiness Directive (AD) 94-18-04 R1, which currently applies to all Univair Aircraft Corporation (Univair) Models Alon A-2 and A2-A; ERCO 415-C, 415-CD, 415-D, 415-E, and 415-G; Forney F-1 and F-1A; and Mooney M10 airplanes. AD 94-18-04 R1 requires installing inspection openings in the outer wing panels, inspecting (one-time) the wing outer panel structural components for corrosion, and repairing any corroded wing outer panel structural component. Several reports of corrosion in the outer wing panels of the affected airplanes prompted that AD. This AD is the result of additional reports of corrosion on airplanes in compliance with AD 94- 18-04 R1. This AD makes the inspection required in AD 94-18-04 R1 repetitive. We are issuing this AD to prevent wing damage caused by a corroded wing outer panel structural component, which, if not detected and corrected, could progress to the point of structural failure. DATES: This AD becomes effective on December1, 2003. The Director of the Federal Register previously approved the incorporation by reference of Univair Aircraft Corporation Service Bulletin No. 29, Revision B, dated January 2, 1995, as of March 24, 1995 (60 FR 13626, March 14, 1995). The Director of the Federal Register approved the incorporation by reference of Univair Aircraft Corporation Mandatory Service Bulletin No. 29, Revision C, dated July 8, 1999, as of December 1, 2003.
79-20-07: 79-20-07 PIPER AIRCRAFT CORPORATION: Amendment 39-3573. Applies to the following Piper Models of airplanes, equipped with three 12 volt cigar lighters powered through a triplet of voltage dropping resistors, certificated in all categories; PA-31 and PA-31-325, S/N 31- 7712074 through 31-7912098 and PA-31-350, S/N 31-7752096 through 31-7952197. Compliance is required within the next 25 hours time in service or 30 days, whichever occurs first, after the effective date of this AD unless already accomplished. To prevent smoke in the cockpit, accomplish the following: a. For Models PA-31 and PA-31-325, S/N 31-7712074 to, but not including, 31- 7912001, and PA-31-350, S/N 31-7752096 to, but not including, 31-7952001; disconnect wire CIG-1 from the 7 amp circuit breaker located at the voltage dropping resistor assembly under the instrument panel or disconnect wire CIG-1A from the 15 amp "Heater and Cigar Lighter" circuit breaker located on the pilot's circuit breaker panel. b. For Models PA-31 and PA-31-325, S/N 31-7912001 through 31-7912098, and PA-31-350, S/N 31-7952001 through 31-7952197, except 31-7952191, 31-7952193, 31- 7952195; disconnect wire CIG-1 from the 7 amp "Lighter" circuit breaker located on the pilot's circuit breaker panel. c. After disconnection, protect the wire by insulating its disconnected end and fold the wire end back against itself or the bundle in which it is routed and secure it. Compliance with the provisions of this Airworthiness Directive may be accomplished in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern region. This amendment is effective October 2, 1979.
65-03-03: 65-03-03 LYCOMING: Amdt. 39-460, Part 39- Federal Register February 2, 1965. Applies to Model IO- 320-BIA Engines Equipped with Hartzell HC-E2YL-2/7663-4 Propellers and Installed in Piper Model PA-30 Aircraft. Compliance required as indicated. To prevent crankshaft flange failure with a possible loss of propeller accomplish the following: (a) Add the following operating limitation to the airplane flight manual: Do not exceed 2,100 r.p.m. engine speed when demonstrating or practicing power-on-stalls. (b) Inspect engines in accordance with the procedure described in 2(a) and 2(b) of Lycoming Service Bulletin No. 300A before further flight following any flight involving acrobatic maneuvers (including spins) which are prohibited by the airplane placard and flight manual or any flight during which the limitation specified in (a) has been exceeded. If cracks are found in the crankshaft flange remove the crankshaft from service before further flight. NOTE: It is requested that any cracks found as the result of the inspections required by this AD be reported to the Engineering and Manufacturing Branch, FAA Eastern Region, John F. Kennedy International Airport, Jamaica, New York. This supersedes AD 64-15-05. This directive effective January 30, 1965. Revised August 5, 1967.
2003-05-10R1: This amendment revises an existing airworthiness directive (AD), that applies to General Electric Company (GE) CF34-3A1, -3B, and -3B1 turbofan engines with scavenge screens part numbers (P/Ns) 4047T95P01 and 5054T86G02 installed in the B-sump oil scavenge system. That AD currently requires initial and repetitive visual inspections and cleaning of the B-sump scavenge screens until a screenless fitting is installed. This amendment requires the same initial and repetitive visual inspections and cleaning of the B-sump scavenge screens until a screenless fitting is installed. This amendment also corrects a typographical error, and introduces a less restrictive terminating action schedule. This amendment is prompted by the need to correct a typographical error and by the need to introduce a less restrictive terminating action schedule. We are issuing this AD to prevent B-sump scavenge screen blockage due to coking which could result in ignition of B-sump oil in the secondary air system, fan drive shaft separation, and uncontained engine failure.
79-19-09: 79-19-09 PIPER: Amendment 39-3560. Applies to Model PA-31T1, Serial Nos. 31T-7804001 to 31T-7904016 inclusive, and PA-31T, Serial Nos. 31T-7400002 to 31T-7920036, inclusive. To prevent possible hazards in flight caused by a shorting of the electroluminescent panel inverters creating smoke in the cockpit: (a) Within the next 100 hours in service or at the next scheduled inspection, whichever occurs first, comply with the instructions of Piper Service Bulletin No. 640 dated June 22, 1979, for the replacement and/or relocation of the electroluminescent panel power supply inverter. (b) Upon request with substantiating data submitted through an FAA Maintenance Inspector, the compliance time specified in this AD may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective September 25, 1979.
2020-18-16: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200, -300, -300F, and -400ER series airplanes. This AD was prompted by the FAA's analysis of the Model 767 fuel system reviews conducted by the manufacturer. This AD requires modifying the fuel quantity indicating system (FQIS) to prevent development of an ignition source inside the center fuel tank due to electrical fault conditions. This AD also provides optional actions for cargo airplanes. The FAA is issuing this AD to address the unsafe condition on these products.
2020-20-12: The FAA is adopting a new airworthiness directive (AD) for all General Electric Company (GE) GEnx-1B64, -1B64/P1, -1B64/P2, -1B67, - 1B67/P1, -1B67P2, -1B70, -1B70/75/P1, -1B70/75/P2, -1B70/P1, -1B70/P2, -1B70C/P1, -1B70C/P2, -1B74/75/P1, -1B74/75/P2, -1B76/P2, and -1B76A/P2 model turbofan engines. This AD was prompted by reports of combustor case burn-through. This AD requires installation of electronic engine control (EEC) software, version B205 or later. The FAA is issuing this AD to address the unsafe condition on these products.
61-26-02: 61-26-02 CANADAIR: Amdt. 379 Part 507 Federal Register December 21, 1961. Applies to all CL-44D4 aircraft. Compliance required as indicated. As a result of a fuel leak found in the line to the upper heater, the following inspection must be accomplished within the next 25 hours' time in service after the effective date of this AD unless already accomplished within the last 40 hours' time in service and at intervals of 65 hours' time in service thereafter. With full fuel pressure in the tail heater fuel lines, inspect all fuel lines and fittings in the tail heater compartment for leaks and security of attachment. Loose lines shall be properly secured, and defective lines and fittings replaced prior to further flight. The special inspections required by this airworthiness directive may be discontinued after incorporation of the Canadian Department of Transport and FAA approved modification. Upon request of the operator an FAA maintenance inspector subject to priorapproval of the Chief, Engineering and Manufacturing Branch, International Division, Washington 25, D.C., may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. This directive effective December 21, 1961.
2003-20-11: This amendment supersedes an existing airworthiness directive (AD) for Eurocopter Deutschland GmbH (ECD) Model EC135 P1 and EC135 T1 helicopters. That AD currently requires adding the AD or a statement to the Rotorcraft Flight Manual (RFM) informing the pilot to reduce power and land as soon as practicable if a thump-like sound followed by unusual vibration occurs during flight. That AD also requires visually inspecting the main rotor drive torque strut assembly (strut) for a crack or a break, recording the inspections in the historical or equivalent record, and re-marking and relocating the strut, as appropriate, and replacing any unairworthy strut with an airworthy strut. Also, that AD establishes life limits for certain struts and revises the life limit for other struts. This amendment retains the same requirements but adds the ECD Model EC135 P2 and EC135 T2 helicopters to the applicability and requires replacing certain life-limited struts with titanium struts. This amendment is prompted by the manufacture of a titanium strut that provides a permanent correction to the unsafe condition that led to limiting the life of other struts that have failed. The actions specified by this AD are intended to prevent failure of a strut and subsequent loss of control of the helicopter.
94-17-16: This amendment supersedes an existing airworthiness directive (AD), applicable to General Electric Aircraft Engines (GEAE) CT7 series turboprop engines, that currently requires a one-time ultrasonic inspection of a suspect population of propeller shafts for metallurgical defects, and if necessary, replacement with a serviceable part. This amendment extends the compliance time for the required ultrasonic inspection on certain propeller shafts. This amendment is prompted by information indicating that the equipment necessary to perform the ultrasonic inspection is less available than originally assumed. The actions specified by this AD are intended to prevent failure of the propeller shaft, which can result in separation of the propeller from the propeller shaft and possible damage to the aircraft.