Results
2001-22-18: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce, plc models Tay 650-15 and 651-54 turbofan engines. This amendment requires initial and repetitive visual and ultrasonic inspections of fan blades for cracks, and, if necessary, replacement with serviceable parts. In addition, this AD requires recording instances when engines are operated in a stabilized manner in newly prohibited ranges. This amendment is prompted by reports of fan blade failures. The actions specified by this AD are intended to prevent fan blade failures, which can result in an uncontained engine failure, engine fire, and damage to the airplane.
75-11-04: 75-11-04 UNITED AIRCRAFT: Amendment 39-2207. Applies to all United Aircraft of Canada Limited PT6A-6, -6A, -6B, -6/C20, -20, -20A, -20B, -27, -28, -34 series turbo-prop engines and PT6B-9 turboshaft engines, incorporating an unmodified power turbine shaft housing assembly part number 3010548. Compliance required as indicated. To aid the early detection, and thereby prevention of PT6A or PT6B engine distress especially in the reduction gearbox of engines incorporating power turbine shaft housing assembly part number 3010548 yet unmodified, accomplish the following: For the PT6A-20, -20A, -20B, -6/C20 engines affected, compliance required within the next fifty hours in service after effective date of this AD. For the PT6A-6, -6A, -6B, -27, -28, -34 and PT6B-9 engines affected, compliance required at the next engine overhaul shop visit, but no later than 3500 hours in service after effective date of this AD. 1. Unless previously accomplished, remove the reduction gearbox oil drain plug part number MS9015-08 and discard the preformed packing part number MS9388-115. Install magnetic chip detector part number 3014794 or 3019373 with a new preformed packing part number MS9388-115 and torque to 45 to 55 lb. in. and lockwire. Install cap part number MS25043-12D or connector part number MS3106-R-12S-3S with connected electrical wiring suitably supported and leading out to a more accessible area within the engine nacelle enclosure. 2. Within the next twenty-five hours in service after installation of the magnetic chip detector and every twenty-five hours in service thereafter, check magnetic chip detector for electrical continuity using any utility ohmmeter. If a resistance of 100 ohms or less is indicated, remove and clean the magnetic chip detector, and inspect the main engine oil filter in accordance with AD 75-06-01. Aircraft may be flown to a base for performance of maintenance required by this AD per FAR 21.197 or FAR 21.199. Upon submission of substantiating data through an FAA maintenance inspector, the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, may adjust the repetitive inspection times specified in this Airworthiness Directive. This amendment is effective May 20, 1975.
87-03-06 R1: 87-03-06 R1 BEECH: Amendment 39-5513 as amended by Amendment 39-5557. Applies to Model 99, 99A, A99A, B99 and C99 (Serial Numbers U-1 thru U-240); 100 and A100 (Serial Numbers B-1 thru B-247); and B100 (Serial Numbers BE-1 thru BE-137), airplanes certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To detect looseness of the elevator outboard hinge attachment to the stabilizer and prevent loss of integrity of the hinge attachment, accomplish the following: (a) Upon the accumulation of 1000 hours total time-in-service (TIS) or within the next 100 hours TIS after the effective date of this AD, whichever comes later, and thereafter at intervals not to exceed 100 hours TIS for Model 99 Series or 150 hours TIS for Model 100 Series airplanes, visually inspect each elevator outboard hinge attachment as follows: (1) Hold the elevator steady at the trailing edge. (2) Push up and down onthe elevator leading edge and visually inspect for movement of the elevator hinge bearing bracket. (b) If movement of the hinge bearing bracket is detected in (a)(2) above, prior to further flight, replace the hinge attach rivets with bolts in accordance with the instructions in Beech Service Bulletin No. 2132, revised December 1986. (c) Unless previously required by paragraph (b) of this AD, on all airplanes with more than 1000 hours total TIS, within the next 600 hours TIS after the initial inspection required by paragraph (a) of this AD, install bolts in place of the four hinge attach rivets in accordance with the instructions in Beech Service Bulletin No. 2132 revised December 1986. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued after bolts have been installed per paragraphs (b) or (c). (e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (f) The repetitive inspection intervals, required by this AD may be adjusted up to 10 percent of the specified interval so as to coincide with other scheduled maintenance. (g) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, 9709 East Central, P.O. Box 85, Wichita, Kansas 67201; or the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Amendment 39-5513 became effective on February 20, 1987. This amendment, 39-5557, becomes effective March 12, 1987.
2017-10-20: We are adopting a new airworthiness directive (AD) for certain Piper Aircraft, Inc. Models PA-31, PA-31-300, PA-31-325, and PA-31-350 airplanes. This AD was prompted by fatigue cracking in the fuselage station (FS) 332.00 bulkhead common to the horizontal stabilizer front spar attachment. This AD requires repetitive inspections to detect cracks in the bulkhead and any necessary repairs. This AD also provides an optional modification if no cracks are found that will greatly reduce the likelihood of the specified cracks. We are issuing this AD to correct the unsafe condition on these products.
2017-09-09: We are adopting a new airworthiness directive (AD) for certain Zodiac Seats California LLC seating systems. This AD was prompted by a determination that the affected seating systems may cause serious injury to the occupant during forward impacts when subjected to certain inertia forces. This AD requires removing affected seating systems. We are issuing this AD to address the unsafe condition on these products.
2001-22-16: This amendment supersedes Airworthiness Directive (AD) 95-02-18, which applies to certain Raytheon Aircraft Company (Raytheon) Beech Models 1900, 1900C (C-12J), and 1900D airplanes. AD 95-02-18 requires you to repetitively inspect the engine truss assemblies for cracks, repair or replace any cracked engine truss assembly, and install reinforcement doublers. This AD requires engine truss assembly replacement, periodic inspections and replacements, and the eventual incorporation of a cowling support installation kit as terminating action. The repetitive inspections of AD 95-02-18 will be retained until mandatory engine truss assembly replacement. This AD is the result of continued reports of fatigue cracks found on engine trusses on airplanes in compliance with AD 95-02-18. The actions specified by this AD are intended to detect and correct cracked engine truss assemblies, which could result in failure of the engine truss assembly and consequent loss of airplane control.
75-09-13: 75-09-13 TELEDYNE CONTINENTAL MOTORS: Amendment 39-2178. Applies to the following Teledyne Continental Motors Model engines manufactured prior to August 10, 1973, installed on, but not necessarily limited to Cessna T-310, 320, 340, 401, 402, 411, 414 and 421 series, Rockwell International Model Aero Commander 685 and Beech V35-TC, V35A-TC and V35B-TC series airplanes: New Engine Remanufactured Engine Engine Model Serial Number Serial Number TSIO-470-B Applies to all S/N's 100080 and below TSIO-470-C Applies to all S/N's 108534 and below TSIO-470-D Applies to all S/N's 138544 and below TSIO-520-B 500018 and below *176191 and below TSIO-520-D 505001 and below *180029 and below TSIO-520-E 502125 and below 182395 and below GTSIO-520-C 602001 and below 155370 and below GTSIO-520-D 601005 and below 219161 and below GTSIO-520-H *600137 and below 218046 and below GTSIO-520-F 603028 and below 224203 and below Model Airplane on Airplane Engine Model Which Installed Serial Numbers TSIO-520-J Cessna 414 00489 and below TSIO-520-K Cessna 340 00318 and below *The following individual engines are not affected by this AD: TSIO-520-B, S/N's 176170, 176185, 176186, 176187; TSIO-520-D, S/N 180028; GTSIO-520-H, S/N 600119. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. (1) To detect cracked turbocharger oil inlet adapters inspect the turbocharger oil inlet adapter located at the turbocharger center housing for cracks and/or oil seepage. If there is evidence of oil leakage or cracks, the adapter must be replaced with steel adapter TCM P/N 640793 or Cessna P/N 5655204-2. When replacing the aluminum adapter with the steel adapter on the following model airplanes, the oil fitting which mates with the turbocharger oil inlet adapter must be replaced, unless already accomplished, with the appropriate steel fitting listedbelow. Applicable Replacement Make Model Airplane S/N's Steel Fitting Beech V35-TC All AN 816-6 V35A-TC AN 816-6 V35B-TC AN 816-6 Cessna 320-D, -E All MS20823-6 320-F 320F0001 thru MS20823-6 320F0034 401 & 402 0001 thru 0155 MS20823-6 (2) If there is no evidence of cracks or oil seepage, inspect at intervals not to exceed 25 hours' time in service from the last inspection until replaced with turbocharger oil inlet adapter TCM P/N 640793 or Cessna P/N 5655204-2. Replacement of the aluminum adapter TCM P/N 628675 or Cessna P/N 5655204-1 with steel adapter P/N 640793 or Cessna P/N 5655204-2 or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, is required within one year from the effective date of this AD. This amendment becomes effective April 24, 1975.
84-12-03: 84-12-03 CASA: Amendment 39-4880. Applies to CASA Model 212 series airplanes, certificated in all categories, as indicated in the applicability statement of each of the following service bulletins. Compliance is required within the time interval specified in each of the following paragraphs after the effective date of this AD, unless already accomplished: A. To prevent damage to the D.C. generating circuit, within the next 200 hours time in service, install a new 5 amp fuse and replace the existing 50 amp fuse with a 35 amp fuse in accordance with CASA Service Bulletin 212-24-22 dated November 7, 1979. B. To prevent the loss of rudder and elevator control, within the next 200 hours time in service, replace the rudder and elevator-to-shaft attach fittings with new design fittings in accordance with CASA Service Bulletin 212-27-12, Revision 3, dated June 12, 1980. C. To prevent damage to the wing flap actuation system, within the next 200 hours time in service, replace the hydraulic cylinder with a new design cylinder in accordance with CASA Service Bulletin 212-27-13 dated December 17, 1980. D. To prevent interference with flight controls, within the next 200 hours time in service, modify the flight deck floor structure in accordance with CASA Service Bulletin 212-27- 14 dated November 18, 1980. E. To prevent damage to the wing flap hydraulic system, within the next 200 hours time in service, replace the hydraulic system relief valve with a new design valve in accordance with CASA Service Bulletin 212-27-15, Revision 1, dated November 30, 1981. F. To prevent bearing failures, within the next 200 hours time in service, replace the existing wing flap control hinge bearings with a stainless steel bearing in accordance with CASA Service Bulletin 212-27-19 dated July 1, 1982. G. To prevent relative displacement between the elevator shaft support fittings and the elevator shaft, within the next 500 hours time in service, install safety rings in accordance with CASA Service Bulletin 212-27-23 dated October 7, 1982. H. To prevent the risk of a fire from fuel collecting forward of the nacelle fire wall, within the next 500 hours time in service, install electric fuel shutoff valves in accordance with CASA Service Bulletin 212-28-11, Revision 1, dated September 2, 1981. I. To ensure proper joint strength, within the next 200 hours time in service, replace the existing nuts in the outer wing-to-center section splice in accordance with CASA Service Bulletin 212-51-01 dated July 7, 1981. J. To ensure proper fitting, within the next 200 hours time in service, replace the existing mount bolts with longer bolts in accordance with CASA Service Bulletin 212-51-02 dated September 22, 1981. K. To ensure proper rudder travel, within the next 200 hours time in service, replace the rudder hinge fittings with new fittings in accordance with CASA Service Bulletin 212-55-07 dated July 1, 1982. L. To prevent damage to the wing flap structure, within the next 200 hours time in service, retorque the attachment fitting fasteners in accordance with CASA Service Bulletin 212- 57-12 dated September 22, 1981. M. To ensure engine fire wall integrity, within the next 200 hours time in service, reduce the clearance space between the engine screen control rods and the firewall at the penetration point in accordance with CASA Service Bulletin 212-73-03, Revision 1, dated July 14, 1982. N. 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. O. 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 July 23, 1984.
2001-22-14: This amendment adopts a new airworthiness directive (AD) that applies to certain Overland Aviation Services (OAS) fire extinguishing system bottle cartridges that were distributed during a certain time period and are installed on aircraft. This AD requires you to remove from service any of these fire extinguishing system bottle cartridges. This AD is the result of several incidents where the fire extinguishing system bottle cartridges activated with excessive energetic force. In one instance, the discharge valve outlet screen fractured and the screen material went through the distribution manifold. The actions specified by this AD are intended to prevent damage to fire extinguishing system components caused by a fire extinguishing system bottle cartridge activating with excessive energetic force, which could result in the fire extinguishing system operating improperly.
2017-11-01: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, and -200C series airplanes. This AD is intended to complete certain mandated programs to support the airplane reaching its limit of validity (LOV) of the engineering data that support the established structural maintenance program. This AD requires various repetitive inspections for cracking of certain lugs on the rear spar and horizontal stabilizer, related investigative and corrective actions if necessary, and replacement of the center section rear spar upper chord as applicable. We are issuing this AD to address the unsafe condition on these products.