Results
75-16-16: 75-16-16 ISRAEL AIRCRAFT INDUSTRIES, LTD: Amendment 39-2290. Applies to Israel Aircraft Industries Jet Commander Models 1121, 1121A and 1121B, and Westwind Model 1123 airplanes certificated in all categories having autopilot vertical reference component Collins P/N 332D-11/522-3985-001 or Collins P/N 332D-11A/792-6694-001 or both, installed in an unpressurized area. Compliance is required as indicated unless already accomplished. To prevent loss of attitude information and improper operation of the autopilot, accomplish the following: (a) Before further IFR or night flight, install a placard on the instrument panel in full view of the pilot to read, "Cross Check Attitude Indicators with Third Attitude Indicator to Detect Unflagged Failures". (b) Within the next 100 hours' time in service, after the effective date of this AD, modify the vertical reference (Collins P/N 332D-11/522-3985-001, or Collins P/N 332D-11A/ 792-6694-001), in accordance with Collins ServiceBulletin No. 9, dated May 1, l974, or an FAA-approved equivalent. (c) The placard required by paragraph (a) of this AD may be removed when the modification required by paragraph (b) has been accomplished. This amendment becomes effective August 12, 1975.
2000-22-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain International Aero Engines AG (IAE) V2500-A5 and -D5 series turbofan engines, identified by serial number. This amendment requires the removal of engines assembled with an improper High Pressure Turbine (HPT) module configuration from service prior to accumulating 5,100 or 7,600 cycles in the improper configuration, or at the next shop visit, depending on the type of improper HPT configuration, and restoration to type design. This amendment is prompted by reports of engines that do not conform to the engine type design, which could cause a Low Cycle Fatigue (LCF) life reduction of the HPT stage 1 disk. The actions specified by this AD are intended to restore engines to type design configuration and to prevent possible LCF failure of the HPT stage 1 disk, which could result in an uncontained engine failure and damage to the airplane.
2013-20-11: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that oxygen generators installed on a certain batch of passenger emergency oxygen container assemblies might become detached by extreme pulling of the mask tube at the end of the oxygen supply causing a high temperature oxygen generator and mask to fall down. This AD requires modifying the passenger emergency oxygen container assembly. We are issuing this AD to prevent a high temperature oxygen generator and mask from falling down and possibly resulting in an ignition source in the passenger compartment, injury to passengers, and reduced availability of supplemental oxygen.
74-18-01: 74-18-01 MCDONNELL DOUGLAS: Amendment 39-1927 as amended by Amendment 39-2533. Applies to all Douglas Aircraft Company DC-10-10/-30/-40 Series airplanes which incorporate Douglas DC-10 Service Bulletin 21-68 or Service Change 1545 when inertial navigation systems are installed. \n\n\tCompliance required as indicated, unless previously accomplished. \n\n\tWithin 300 additional hours time in service after the effective date of this AD, either \n\n\t(1)\tIncorporate in the FAA-approved Airplane Flight Manual, Documents MDC-J1010, MDC-J1030, MDC-J5830, MDC-J1040, and Appendix X of MDC-J1010, the following revision in Section I, Limitations, under the existing heading 'Cabin Pressurization': \n\n\t'For the inertial platform configured airplanes, temporary installation of wiring per Douglas Drawing WBP 9502 must be accomplished for planned unpressurized flight'; or \n\n\t(2)\tIncorporate other airplane flight manual revisions, and/or equipment modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tAmendment 39-1927 became effective August 26, 1974. \n\n\tThis amendment 39-2533 becomes effective March 8, 1976.
52-04-01: 52-04-01: MARTIN: Applies to All Models 202 Aircraft. Compliance required not later than May 1, 1952. Provide adequate drain for throttling valve vent in the cabin heater fuel supply line.
2025-06-01: The FAA is adopting a new airworthiness directive (AD) for all Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. This AD was prompted by a design review that discovered software protection logic for potential large leaks from the engine bleed duct inside the engine core compartments was partially impaired. This AD requires revising the existing airplane flight manual (AFM) to incorporate the procedures for the flightcrew to manually isolate the opposite functional engine in the event of an engine bleed duct large leak condition, as specified in a Transport Canada AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2013-20-14: We are adopting a new airworthiness directive (AD) for certain the Boeing Company Model 747-400 and -400F series airplanes. This AD was prompted by a report of cracks on airplanes prior to line number 1308 in the forward and aft inner chords of the station (STA) 2598 bulkhead, and the bulkhead upper and lower webs. This AD requires, as applicable, repetitive high frequency eddy current (HFEC) and low frequency eddy current (LFEC) inspections for cracks in the splice fitting, support frame, forward and aft inner chords, floor support, bulkhead upper web on the upper left and right side of the bulkhead, and the bulkhead lower web on the lower left side of the bulkhead and repair if necessary; and repetitive post-repair inspections and repair if necessary. We are issuing this AD to detect and correct cracks in the splice fitting, support frame, floor support, forward and aft inner chords, and the bulkhead upper and lower webs of the STA 2598 bulkhead, which could adversely affectthe structural integrity of the airplane.
75-04-09: 75-04-09 MOONEY: Amendment 39-2091 as amendment by Amendment 39-2127. Applies to Models M20C, M20E, and M20F airplanes manufactured after October 1974 with the following serial numbers on which the landing gear actuator, P/N LA11C2110, manufactured by International Telephone and Telegraph Corporation, is installed: Model M20C: 20-0037, 0038, 0039, 0040, 0041, 0042, 0043, 0044, 0045, and 0046; Model M20E: 21-0050, 0051, 0052, 0053, 0054, 0055, 0056, 0057, 0058, 0059, and 0060; Model M20F: 22-0065, 0066, 0067, 0068, 0069, 0070, 0071, 0072, 0073, 0074, 0075, 0076, 0077, and 0078. Compliance is required prior to further flight except that airplanes may be flown to a facility for actuator replacement after fixing the landing gear in the extended position in accordance with instructions included in Mooney Aircraft Corporation Service Bulletin M20-191, dated January 28, 1975, or later FAA approved revision, or an FAA approved equivalent procedure. To prevent further failures, replace the International Telephone and Telegraph Corporation P/N LA11C2110 landing gear actuator with a Mooney Aircraft Corporation P/N 950227-501 landing gear actuator in accordance with Mooney Aircraft Corporation Service Bulletin M20-191, dated January 28, 1975, or later FAA approved revision, or by an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. Amendment 39-2091 became effective on February 20, 1975. This amendment 39-2127 becomes effective on March 20, 1975.
73-14-03: 73-14-03 BEECH: Amendment 39-1679. Applies to: 1) Paragraphs A and C of the AD are applicable to: Model F33A (Serial Numbers CE-400 through CE-414, CE-416 through CE- 426, CE-428 and CE-432); Model F33C (Serial Numbers CJ-31 (CD-1305) through CJ-39 (CD- 1313)); Model V35B (Serial Numbers D-9389 through D-9406, D-9408 through D-9454 and D- 9464); Model A36 (Serial Numbers E-362 through E-367, E-369 through E-389, E-392 through E-409, E-415, E-417 and E-418); Models 95-B55 and 95-B55A (Serial Numbers TC-1484, TC-1486 through TC-1533, TC-1538, TC-1542 and TC-1544); Models E55 and E55A (Serial Numbers TE-880, and TE-882 through TE-907); Models 58 and 58A (Serial Numbers TH-264, TH-266 through TH-310, TH-315 and TH-318). Applies to: 2) Paragraphs A, B, and C of the AD are applicable to: Model F33A (Serial Numbers CE-427, CE-430 and CE-431); Model V35B (Serial Numbers D-9455 through D-9460 and D-9462); Model A36 (Serial Numbers E-410 through E-414 and E-416); Models 95-B55 and 95-B55A (Serial Numbers TC-1534 through TC-1537); Models E55 and E55A (Serial Numbers TE-908, TE-909 and TE-910); Models 58 and 58A (Serial Numbers TH-311 through TH-314 and TH-316). Compliance: Required as indicated, unless already accomplished per Beechcraft Service Instructions 0579-200 or later FAA-approved revisions. To check landing gear shock strut pistons for proper hardness, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: A) Using a portable hardness tester, measure the hardness of the nose gear shock strut piston in an area from 1 inch to 4 inches above the nose wheel fork. The allowable hardness range is from Rockwell Scale C38 to C46 1/2. If during the hardness measuring process a reading appears unreliable, make additional measurements at other spots but within the 1 inch to 4 inch area specified herein until an accurate measurement is obtained. B) Using a portable hardness tester, measure the hardness of both main gear shock strut pistons in an area 1 inch to 4 inches above the axle socket. The allowable hardness range is from Rockwell Scale C43 1/2 to C50 1/2. If during the hardness measuring process a reading appears unreliable, make additional measurements at other spots but within the 1 inch to 4 inch area specified herein until an accurate measurement is obtained. C) If a hardness measurement is outside of the hardness range specified in Paragraphs A and/or B of this AD, prior to further flight, replace any defective landing gear shock strut piston with an airworthy piston, except that the airplane may be flown in accordance with FAR 21.197 to a base where the replacement can be performed, provided the landing gear remains down and locked. This amendment becomes effective July 6, 1973.
2013-21-01: We are adopting a new airworthiness directive (AD) for Eurocopter Model AS350B, AS350BA, AS350B1, AS350B2, AS350B3, AS350C, AS350D, AS350D1, AS355E, AS355F, AS355F1, AS355F2, AS355N, and AS355NP helicopters. This AD requires certain inspections of each tail rotor pitch horn assembly (pitch horn) for a crack, and if there is a crack, before further flight, replacing the pitch horn with an airworthy pitch horn. This AD is prompted by a report of a crack in the yoke of a pitch horn. These actions are intended to detect a crack in the pitch horn to prevent failure of the pitch horn, loss of the anti-torque function, and subsequent loss of control of the helicopter.