Results
72-02-06: 72-02-06 MITCHELL INDUSTRIES, INC., doing business as EDO-AIRE MITCHELL: Amdt. 39-1383. Applies to Mitchell automatic pilot instruments installed in various Cessna aircraft in accordance with the following Supplemental Type Certificates: AUTOPILOT MODEL STC NUMBER AIRCRAFT MAKE AND MODE AK086 SA20SW Cessna 210B and C AK086R SA20SW Cessna 210B and C AK086E SA20SW Cessna 210B and C AK088 SA27SW Cessna 182E and F AK088R SA27SW Cessna 182E and F AK088E SA27SW Cessna 182E and F AK110 SA101SW Cessna 182E, F and G AK110E SA101SW Cessna 182E, F and G AK110E-3 SA101SW Cessna 182E, F and G AK112 SA89SW Cessna 210B and C AK120 SA149SW (Cessna 210-5, 210-5A,) AK120E SA149SW ( 206, P206, ) AK120E-3 SA149SW ( and U206, ) AK126 SA330SW Cessna 210D and E AK126E SA330SW Cessna 210D and E AK126E-3 SA330SW Cessna 210D and E AK154 SA489SW Cessna 182H AK154E SA489SW Cessna 182H AK154E-3 SA489SW Cessna 182HAK155 SA491SW Cessna 337 AK155E SA491SW Cessna 337 AK155E-3 SA491SW Cessna 337 Compliance required within the next ten (10) hours' time in service after the effective date of this AD, unless already accomplished. To prevent fatigue failure of the control wheel shaft with possible resultant loss of aileron and elevator control, accomplish the following: Remove the Mitchell automatic pilot instrument servo, inspect the control wheel shaft, take corrective action as necessary, and reassemble in accordance with Edo-Aire Mitchell Service Bulletin No. MB-6 dated October 29, 1971, or later FAA approved revision, or any other method approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. NOTE: The Mitchell automatic pilot instrument servo may be reinstalled in accordance with Edo-Aire Mitchell Service Letter ML-32 dated December 22, 1971, or later FAA approved revision, or any other methodapproved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. The bulletin and letter mentioned herein may be obtained from Edo-Aire Mitchell, P. O. Box 610, Mineral Wells, Texas 76067. This amendment becomes effective January 31, 1972.
2004-03-26: This amendment adopts a new airworthiness directive (AD), applicable to certain Dassault Model Falcon 900EX series airplanes, that requires modification of the front attachment area of the No. 2 engine. This action is necessary to prevent failure of the fail-safe lugs of the hoisting plate of the forward engine mount, and subsequent cracking of the pick-up folded sheet of the pylon forward rib. Such cracking could rupture the mast case box, which could result in loss of the two forward engine mounts and consequent separation of the engine from the airplane. This action is intended to address the identified unsafe condition.
75-04-05: 75-04-05 ROCKWELL INTERNATIONAL: Amendment 39-2087. Applies to all NA- 265 Series Airplanes certificated in all categories. Compliance as indicated, unless already accomplished. To provide protection in the event of an unknown incipient failure condition in the engine fuel pressure switch, Hydra-Electric Co. P/N 12251, accomplish the following: (a) Within 10 hours' time in service after the effective date of this AD, inspect the engine fuel pressure switches for fuel seepage or leakage. (1) If seepage or leakage is found, replace the failed switch before further flight, in accordance with Sabreliner Service Bulletin 74-34, dated January 15, 1975, revised January 24, 1975, or later FAA-approved revisions. (2) If seepage or leakage is not found, repeat the inspection at intervals not to exceed 10 hours' time in service until the inspection and installation described in (b) are accomplished. (b) Within 90 days after the effective date of this AD, conductan inspection to determine the part number of the engine fuel pressure switch installed in accordance with steps 1 through 3 of Sabreliner Service Bulletin 74-34, dated January 15, 1975, revised January 24, 1975, or later FAA-approved revisions. (1) If Hydra-Electric Co. P/N 12251 is found installed, either (i) Accomplish the installation described in steps 4 through 10 of Sabreliner Service Bulletin 74-34, dated January 15, 1975, revised January 24, 1975, or later FAA-approved revisions, prior to further flight; or (ii) Repeat (a) above, until the installation described in (b)(1)(i) is accomplished. The installation required by (b)(1)(i) is to be performed within 90 days after the effective date of this AD. (c) If P/N 1B2522-25 (Aero Instruments Co., or Century Electronics and Instrument Inc., or Hathaway Industries, or Electro Controls Inc.), or P/N 685-1, Value Engineering Products, is installed, proceed with steps 8 through 10 of Sabreliner Service Bulletin74-34, dated January 15, 1975, revised January 24, 1975, or later FAA-approved revisions. (d) Airplanes may be flown to a base for the performance of the inspections and installations required by this AD, per FAR's 21.197 and 21.199, except when seepage or leakage is known to exist. (e) Return P/N 12251 switches removed from service to Rockwell International, Aviation Services Division, Lambert Field, St. Louis, Mo. 63145. (f) Equivalent inspections and installations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. This amendment becomes effective February 18, 1975.
2016-15-06: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by a design review, which found that the burst pressure of the flexible hose used to vent oxygen from the high-pressure relief valve of the oxygen cylinder overboard is lower than the opening pressure of the high-pressure relief valve. This AD requires replacement of flexible relief hoses for the crew oxygen bottles with new metal design relief hoses. We are issuing this AD to prevent the accumulation of excess oxygen in an enclosed space, which could, if near a source of ignition, cause an uncontrolled oxygen-fed fire.
70-26-05: 70-26-05 PRATT & WHITNEY AIRCRAFT: Amdt. 39-1131. Applies to all model JT8D series turbofan engines. Compliance required as indicated. To prevent failure of the first stage compressor rotor blades as the result of improperly machined blade roots, accomplish the following: (a) Within the next 900 hours in service after the effective date of this AD, unless already accomplished, visually inspect all P/N 487801, 511901 change letter L or earlier, 594601 and 616601 change letter B or earlier first stage compressor rotor blades, for tool marks within the radius of the Z plane platform on both sides of the blade root area. If tool marks are observed, replace the blade. (b) Upon submission of substantiating data through an FAA Maintenance Inspector by an owner or operator to the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, compliance time may be adjusted. (Pratt & Whitney letter PSE:HHB:0-4-6-1-33 dated April 6, 1970, pertains to this subject.) This amendment is effective December 29, 1970.
81-10-05: 81-10-05 McDONNELL DOUGLAS: Amendment 39-4104. Applies to McDonnell Douglas Model DC-10 series airplanes, fuselage numbers 1 through 98, except fuselage number 2, certificated in all categories. See McDonnell Douglas Service Bulletin identified below for the applicable aircraft serial numbers. Compliance is required as indicated, unless already accomplished. \n\n\tTo prevent electrical arcing and burning in the electrical connector in the Hydro-Aire fuel pump housing, accomplish the following: \n\n\t(a)\tWithin 300 hours' additional time in service after the effective date of this AD, replace the electrical connectors in the fuel boost/transfer pump housings in those fuel tanks specified, in accordance with paragraph 2, Accomplishment Instructions, McDonnell Douglas Service Bulletin, DC-10 SB 28-17, Revision 2, dated July 27, 1973. \n\n\t(b)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of modifications required by this AD. \n\n\t(c)\tAlternative modifications or other actions which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, FAA Northwest Region. \n\n\tThe manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Director, Publications and Training, C1-750 (54-60). These documents also may be examined at FAA Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108, or 15000 Aviation Boulevard, Hawthorne, California 90261, Room 6W14. \n\n\tThis amendment becomes effective July 22, 1981.
2004-03-04: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes. This AD requires repetitive inspections for cracking in the casing of the nose landing gear (NLG), and corrective action if necessary. This action is necessary to find and fix cracking of the NLG casing, which could result in failure of the NLG, and consequent reduced controllability of the airplane during takeoff and landing. This action is intended to address the identified unsafe condition.
2002-09-03: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (ECF) Model AS332L2 helicopters. This action requires, before further flight, verifying that the air vent is installed on the inflation cylinder of each life raft assembly. If the air vent is missing, this AD also requires replacing the cylinder head with an airworthy part before further flight. This amendment is prompted by the discovery that an inflation cylinder in the life raft did not have an air vent installed. This condition, if not corrected, could result in inadvertent life raft inflation, loss of the life raft, contact with the main or tail rotor, and subsequent loss of control of the helicopter.
81-16-04: 81-16-04 BELLANCA AIRCRAFT CORPORATION: Amendment 39-4172. Applies to Models 8KCAB, 7ECA, 7GCAA, 7GCBC and 7KCAB airplanes certificated in Acrobatic category. \n\n\tTo insure that the competition harness (also referred to as the ACRO harness) is installed properly, accomplish the following before further flight: \n\n\t1.\tUnless previously accomplished, insert figure I of this AD into all applicable aircraft having approved flight manuals. \n\n\t2.\tAttach figure I of this AD to all "Operating Limitation Instructions" (yellow card) for those applicable aircraft where a flight manual is not required (Model 7 Series airplanes). \n\n\t3.\tInspect all competition harness installations to insure that the shoulder straps are installed in accordance with figure I of this AD. Insure that the shoulder straps of the added harness pass on the forward side of the seat back. \n\n\tThis amendment becomes effective July 28, 1981.
2016-15-07: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), Model CL-600-2D15 (Regional Jet Series 705), Model CL-600-2D24 (Regional Jet Series 900), and Model CL-600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports of corrosion found on the slat and flap torque tubes in the slat and flap control system. This AD requires replacement of the slat and flap torque tubes in the slat and flap control system. We are issuing this AD to prevent rupture of a corroded slat or flap torque tube. This condition could result in an inoperative slat or flap system and consequent reduced controllability of the airplane.