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79-26-01: 79-26-01 PIPER: Amendment 39-3639. Applies to Piper PA-23-250 Model airplanes, Serial Nos. 27-7654001 thru 27-7954044 certificated in all categories, which incorporate the following stabilators. Serial Nos.: 0336-L thru 0340-L 0401-L thru 0607-L 0337-R thru 0341-R 0402-R thru 0609-R To prevent possible loosening and relative motion between the stabilator bottom skins and the stabilator frame - structure, accomplish the following: a. Within the next 50 hours in service after the effective date of this AD, unless already accomplished within the past 50 hours and at intervals not to exceed 100 hours in service thereafter, inspect and repair or alter the left and right stabilator in accordance with the "INSTRUCTIONS" section on page 3 of 3 in Piper Service Bulletin No. 606 dated July 12, 1979, or approved equivalent. b. When the stabilator assemblies are altered in accordance with paragraph B.4. of the "INSTRUCTIONS" section or equivalent, compliance with this AD is no longer required. c. Equivalent inspections, repairs or alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. d. Upon submission of substantiating data 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 December 24, 1979.
2020-20-01: The FAA is adopting a new airworthiness directive (AD) for certain Dassault Aviation Model FALCON 7X, FALCON 900EX, and FALCON 2000EX airplanes. This AD was prompted by reports of primary display unit (PDU) data flickering on airplanes equipped with EASy software. This AD requires amending the applicable Dassault airplane flight manual (AFM) to incorporate the applicable AFM change project (CP), as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2009-07-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Incomplete accomplishment instructions in SB [service bulletin] ATR72-27-1059 original issue and Revision 1, failed to mention installation of cotter pins to secure the self locking nuts after re-installation of the modified Pitch Uncoupling Mechanism (PUM), when connecting the elevator control linkage rods to the PUM input levers and the PUM output rods to the elevator bellcranks (on both sides). Because of the non-installation of these four cotter pins, the fail-safe criteria of the design requirements on the pitch control are no longer met. Such a failure could cause the loss of one self locking nut and would result in the loss of pitch control onone side--Captain or First Officer--or the loss of control of one elevator surface. The symmetrical loss of two concerned self-locking nuts could lead to a complete loss of the pitch control. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
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.