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73-19-10: 73-19-10 GRUMMAN AIRCRAFT: Amendment 39-1719 as amended by Amendments 39-1757 and 39-1828 is further amended by Amendment 39-3544. Applies to G-164A S/N's 1 through 1659A and G-164B S/N's 1B through 56B certificated in all categories and all G-164A and G-164B aircraft in which the elevator control horn assembly and torque tube end fittings have not been modified per Gulfstream American Service Note No. 23 or FAA-approved equivalent. Compliance required as indicated. 1. Within the next 25 hours in service or two weeks, whichever occurs first, unless already accomplished within the last 75 hours in service, inspect the bolts attaching the Elevator Control Horn, P/N A 1841-3, to the left and right side elevator, P/N A1201-5A and A1201-4A respectively, for a standard (ref. AC 43.13-1 Chg. 7) torque rating and for corrosion and thereafter at intervals not to exceed 100 hours in service or 60 days, whichever occurs first. 2. If any looseness is detected, the bolts must be removed and inspected for wear. 3. Replace any worn or corroded bolts with bolts of the same part number or NAS 1304-12 bolts or an equivalent as approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, except that the aircraft may be flown in accordance with FAR 21.197. 4. The bolts referenced in paragraph 3, must be replaced at intervals not exceeding 1000 hours in service or one year, whichever occurs first. 5. 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 inspection intervals specified in this AD. 6. The repetitive inspection intervals required by paragraph 1 may be discontinued upon accomplishment of the modification in Grumman Gulfstream Service Note No. 23 dated 8/1/76, or an FAA-approved equivalent. 7. Any equivalent parts or alterations must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. (Grumman American Aviation Corporation AgCat Service Bulletin No. 51 pertains to this subject.) Amendment 39-1719 was effective September 21, 1973. Amendment 39-1757 was effective December 20, 1973. Amendment 39-1828 was effective May 6, 1974. This Amendment 39-3544 is effective August 29, 1979.
2011-27-02: We are adopting a new airworthiness directive (AD) for certain Lockheed Martin Corporation/Lockheed Martin Aeronautics Company Model L-1011-385-1, L-1011-385-1-14, L-1011-385-1-15, and L-1011-385-3 airplanes. This AD was prompted by results from a damage tolerance analysis conducted by the manufacturer indicating that fatigue cracking could occur in wing rear spar and upper surface zones. This AD requires repetitive inspections for cracking of the wing rear spar and upper surface zones, and repair if necessary. We are issuing this AD to detect and correct such fatigue cracking, which could result in cracking that grows large enough to reduce the wing strength below certificated requirements and possibly cause fracture of the rear spar, resulting in extensive damage to the wing and possible fuel leaks.
2011-26-07: We are superseding an existing airworthiness directive (AD) for certain TCM and R-RM series reciprocating engines. That AD currently requires replacement of certain magnetos if they fall within the specified serial number (S/N) range, inspection of the removed magneto to verify that the stop pin is still in place, and, if the stop pin is not in place, inspection of the engine gear train, crankcase, and accessory case. This new AD corrects the range of S/Ns affected, requires the same replacement and inspections, and adds R-RM C-125, C- 145, O-300, IO-360, TSIO-360, and LTSIO-520-AE series reciprocating engines to the applicability. This AD was prompted by our awareness of an error in the previous AD applicability in the range of magneto S/Ns affected and of the need to include certain engines made by R-RM, under license of TCM. We are issuing this AD to prevent engine failure and loss of control of the airplane due to migration of the magneto impulse coupling stop pin out of the magneto frame and into the gear train of the engine.
2006-11-18: We are adopting a new airworthiness directive (AD) for certain Pacific Aerospace Corporation Ltd. Model 750XL airplanes. This AD requires you to inspect the condition of the insulation of the wiring adjacent to the electrical plugs mounted in the left-hand (LH) and right-hand (RH) sides of the forward end of the cockpit center console for signs of abrasion and arcing. If you find any evidence of abrasion or arcing, this AD requires you to replace the affected wire(s) and secure the wires away from the back shells of the electrical plugs. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for New Zealand. We are issuing this AD to detect and correct damaged wires on the LH and RH sides of the forward end of the cockpit center console, which could result in short-circuiting of the related wiring. This could lead to electrical failure of affected systems and potential fire in the cockpit.
94-15-08: This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company Model R22 helicopters. This action requires an initial inspection and repetitive checks and visual inspections for corrosion and cracks on certain main rotor blades. This amendment is prompted by reports of chordwise cracks found in the main rotor blades. The actions specified in this AD are intended to prevent abnormal in-flight vibrations, failure of the main rotor blade, and subsequent loss of control of the helicopter.
2011-26-08: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211-Trent 800 Series Turbofan Engines. 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 fuel leaks from the engine due to damage to sections of the fan case low-pressure (LP) fuel tubes. We are issuing this AD to prevent engine fuel leaks, which could result in risk to the airplane.
2003-21-09 R1: This amendment revises an existing airworthiness directive (AD) for Eurocopter France (ECF) Model AS355E, F, F1, F2, and N helicopters that currently requires certain checks of the magnetic chip detector plug (chip detector) and the main gearbox (MGB) oil-sight glass, certain inspections of the lubrication pump (pump), and replacing \nthe MGB and the pump with an airworthy MGB and pump, if necessary. Also, the AD requires that before an MGB or pump with any hours time- in-service (TIS) can be installed, it must meet the AD requirements. This amendment retains those requirements but limits the applicability to one part number with certain serial-numbered pumps or modified after a certain date. This amendment is prompted by an investigation by the manufacturer that revealed a malfunction occurred after modifying the pump case on certain pumps after major overhaul and repairs. The actions specified by this AD are intended to limit the applicability to certain pumps, to detect sludge on the chip detector, to prevent failure of the MGB pump, seizure of the MGB, loss of drive to an engine and main rotor, and subsequent loss of control of the helicopter.
97-11-10: This amendment adopts a new airworthiness directive (AD) that applies to Puritan Bennett Aero Systems Company (Puritan Bennett) Series 174290 Constant Flow Airline Portable Oxygen Masks, Part Numbers 174290-14, 174290-24, 174290-34, 174290-44, and 174290-54, that are utilized on aircraft. This action requires replacing any Series 174290 Constant Flow Airline Portable Oxygen Masks, Part Numbers 174290-14, 174290-24, 174290-34, 174290-44, and 174290-54, that have a manufacturing date between September 1992 to August 1996 with an FAA-approved mask that incorporates a part number not covered by this AD. These masks have a connector with an orifice that could restrict more than half of the oxygen flow to the passenger. This oxygen mask is mainly used for emergency medical action or emergency decompression procedures during flight. The actions specified by this AD are intended to prevent restricted oxygen flow, which, if not corrected, could cause serious injury to a passengerin need of emergency or first aid oxygen during flight.
63-26-05: 63-26-05 VICKERS: Amdt. 657 Part 507 Federal Register December 21, 1963. Applies to All Viscount Model 810 Series Aircraft. Compliance required as indicated. Fatigue failures have been reported on flap beams in the areas shown in figures 4 and 5 of Vickers Preliminary Technical Leaflet No. 107 Issue 2 (800/810 Series). To preclude further failures accomplish the following on Nos. 1 and 4 flap units: (a) Within 200 landings after the effective date of this AD, on aircraft which have accumulated 10,000 or less landings, unless already accomplished within the past 1,300 landings, conduct dye penetrant or FAA approved equivalent inspection for cracks in accordance with PTL 107 Issue 2. If no cracks are found, reinspect at intervals not exceeding 1,500 landings until the aircraft accumulates between 10,000 and 11,000 landings during which time the airplane must be reinspected. Thereafter, the aircraft must be reinspected at intervals not exceeding 600 landings until atotal of not more than 12,000 landings are accumulated at which time either of the following or FAA approved equivalent must be incorporated: (1) Modification FG.1946, or (2) The repair/reinforcing scheme defined in the referenced PTL. (b) Within 50 landings after the effective date of this AD on aircraft which have attained over 10,000 landings, unless already accomplished within the past 550 landings, conduct the inspection of (a). If no cracks are found, reinspect at intervals not exceeding 600 landings until reinforcing scheme (a)(1) or (a)(2), or FAA approved equivalent, has been incorporated. Incorporate the reinforcing scheme within 2,000 landings after the effective date of this AD. (c) Cracked flap beams are considered acceptable for a further 500 landings provided that the cracks are within the limits specified in "Definition of Serviceability" paragraph 3 of the referenced PTL, and provided that the area is reinspected in accordance with (a) within every 100 landings to ensure that no crack propagation has occurred. Incorporate repair/reinforcing scheme (a)(1) or (a)(2), or FAA approved equivalent, as follows: (1) Within 10 landings from the time of crack detection for aircraft with unacceptable cracks, and within 10 landings for aircraft with cracks that are found to propagate in length. (2) On or before the completion of 500 landings from the time of crack detection for aircraft with acceptable cracks. d) After incorporating the modification of (a)(1) or (a)(2), or FAA approved equivalent, the special inspection of this AD may be discontinued. It will be necessary for the operator to maintain a record of landings in order to ascertain compliance with this AD. If past records are unavailable, the number of landings prior to the effective date of this AD may be estimated by substituting one landing for each hour in service prior to the effective date of this AD. (Vickers-Armstrong PTL No. 107 Issue 2 (800/810 Series) and Modification FG.1948 cover this subject.) This directive effective January 21, 1964.
93-02-15: 93-02-15 AIRBUS INDUSTRIE: Amendment 39-8499. Docket 93-NM-10-AD. Applicability: Model A320 series airplanes, manufacturer's serial numbers (MSN) 263 to 384, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the failure of the airplane to respond to autopilot commands during autoland, the inability to start the constant speed motor/generator, and the disconnection of battery power during landing gear extension, accomplish the following: (a) Within 100 hours time-in-service after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to include the following statement. This may be accomplished by inserting a copy of this AD, or a copy of Model A320 AFM Temporary Revision 9.99.99/90, Issue 2, dated December 22, 1992, in the AFM. "DUAL APs OPERATION IS MANDATORY FOR AUTOLAND AND CAT 3 APPROACHES AND IS RECOMMENDED FOR ILS APPROACHES UNTIL REPLACEMENT OF POSSIBLE DEFECTUOUS ELECTRICAL TERMINAL BLOCKS." (b) Within 400 hours time-in-service after the effective date of this AD, inspect the terminal blocks installed in the autopilot and the electrical generation systems to determine the date of manufacture, in accordance with Airbus Industrie All Operator Telex 24-02, Revision 1, dated December 23, 1992. (1) If no terminal block with a date code between 9129 and 9149, inclusive, is found, the restriction required by paragraph (a) of this AD may be removed from the AFM. (2) If any terminal block with a date code between 9129 and 9149, inclusive, is found, prior to further flight, replace the defective terminal block with a terminal block having a date code that is not between 9129 and 9149, inclusive, and perform an operational test of the system in which the terminal block is located, in accordance with the AOT. Following accomplishment of these requirements, the restriction required by paragraph (a) of this AD may be removed from the AFM. (c) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (e) The AFM revision shall be done in accordance with Model A320 AFM Temporary Revision 9.99.99/90, Issue 2, dated December 22, 1992; and the inspection, replacement, and testing shall be done in accordance with Airbus Industrie All Operator Telex 24-02, Revision 1, dated December 23, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on March 11, 1993.