Results
2020-20-07: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000-AE3, Trent 1000- CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3, Trent 1000-R3, Trent 7000-72, and Trent 7000-72C model turbofan engines. This AD was prompted by a report of crack findings in the front air seal on the intermediate-pressure compressor (IPC) shaft assembly during the stripping of a flight test engine. This AD requires initial and repetitive borescope inspections (BSIs) or visual inspections of the IPC shaft assembly and, depending on the results of the inspection, replacement of the IPC shaft assembly with a part eligible for installation. The FAA is issuing this AD to address the unsafe condition on these products.
84-02-01: 84-02-01 AIRBUS INDUSTRIE: Amendment 39-4794. Applies to Model A300 B2-1A, B2- 1C, B4-2C, B2K-3C, B4-103, B2-203, and B4-203 series airplanes, certificated in all categories with serial numbers specified in paragraph 1, Planning Information, of Airbus Industrie Service Bulletin A300-32-310, dated February 12, 1981. To prevent potential loss of braking, accomplish the following, unless previously accomplished: A. Within the next 500 flight hours after the effective date of this AD, inspect the hydraulic hose end fitting collars on Titeflex Type 3/8-inch diameter hoses SC641060266 of the brake hydraulic system in accordance with paragraph 2, Accomplishment Instructions, of the service bulletin. 1. End fittings with batch reference number 06K672C,06L039C, or 06M330C on the sleeve or other fittings which are cracked must be replaced with end fittings manufactured after January 1976 and having identification mark "U", within 50 flight hours from the date of inspection.2. Uncracked end fittings with date of manufacture later than January 1976 and no identification mark or identification mark "X" must be replaced with the end fittings types specified in subparagraph A.1, above, within 250 flight hours from the date of inspection. B. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. This amendment becomes effective February 27, 1984.
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.