Results
74-04-05: 74-04-05 CANADAIR: Amdt. 39-1788. Applies to all CL-44D4 and CL-44J airplanes with more than 20,000 hours' time in service. To detect cracks in the main landing gear uplock attachment fitting, P/N 44-10162 and -1, accomplish the following: 1. Within the next 100 hours' time in service after the effective date of this AD, unless accomplished within the last 400 hours' time in service, and at intervals thereafter not to exceed 500 hours' time in service, inspect the main landing gear uplock attachment fitting, P/N 44-10162 and -1 at the four corners of the lug for cracks using a dye penetrant inspection with a glass of at least 10-power or an approved equivalent inspection. 2. Cracked parts must be replaced before further flight, or repaired before further flight as specified in paragraphs 1(a) and (b) of the Inspection Procedure of Canadair's Service Information Circular 374-CL-44 or with an approved equivalent repair. 3. The compliance times may be increased by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, upon receipt of substantiating data submitted through an FAA maintenance inspector. 4. Equivalent inspections, parts or repairs must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective February 20, 1974.
2003-09-07: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas transport category airplanes listed above, that requires a check of the slant pressure panels of the wheel wells of the left and right main landing gear (MLG) for water leakage, and repair of any leak found. This action is necessary to prevent the accumulation of water in the wheel wells of the MLG during flight, which could freeze on the lateral control mixer and control cables, resulting in restricted lateral control and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
99-21-27: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model DHC-8-311 and -315 series airplanes, that currently requires replacement of the nitrogen cylinder assemblies that inflate the airplane s ditching dams with improved nitrogen cylinder assemblies. This amendment expands the applicability of the existing AD. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the ditching dams to inflate fully during an emergency water landing, which could result in water entering the airplane.
2012-23-03: We are adopting a new airworthiness directive (AD) for all Eurocopter France (Eurocopter) Model SA.315B Alouette III, SE.3160 Alouette III, SA.316B Alouette III, SA.316C Alouette III, SA.319B Alouette III, SA 3180-ALOUETTE ASTAZOU, SA 318B-ALOUETTE ASTAZOU, and SA 318 C-ALOUETTE ASTAZOU helicopters. This AD requires inspecting the cage of the free-wheel assembly for the correct alignment of the roller drive pocket recesses and replacing the free-wheel cage with an airworthy free-wheel cage if a defect exists. This AD was prompted by incorrect positioning of the roller drive pocket recesses on the tail rotor drive shaft free-wheel cage, which caused a pilot to experience a heavy jerk in the yaw control during in-flight autorotation training. The requirements of this AD are intended to prevent a loss of tail rotor drive and subsequent loss of control of the helicopter.
75-12-01: 75-12-01 SIKORSKY AIRCRAFT: Amendment 39-2221. Applies to S-61L, S-61N, S- 61R and S-61NM helicopters certificated in all categories including Military type CH-3C, HH- 3C, CH-3E, and HH-3E helicopters equipped with the following main rotor blades: (1) S6115-20501 series, prior to and including S6115-20501-9 main rotor blade assemblies. (2) S6115-20601 series, prior to and including S6115-20601-044 main rotor blade assemblies. (3) S6117-20101 series, prior to and including S6117-20101-053 main rotor blade assemblies. (4) S6188-15001 series, prior to and including S6188-15001-044 main rotor blade assemblies. Compliance required as indicated. (a) Prior to the first flight of each day, inspect each main rotor blade in accordance with Section 2, paragraph C of Sikorsky Service Bulletin No. S61B15-18B or later FAA-approved revisions for possible free counterweights or loose material in the blade spar cavity. If any sound is evident, remove the blade from service immediately and notify Sikorsky Aircraft Product Support Department. (b) If any unusual one-per-rev vibration is noted, inspect each main rotor blade prior to further flight for a possible free counter-weight or loose material in the spar cavity in accordance with Section 2, paragraph C of Sikorsky Service Bulletin No. 61B15-18B or later FAA-approved revisions. If any sound is evident, remove the blade from service immediately and notify Sikorsky Aircraft Product Support Department. (c) Upon request of the operator, equivalent methods of compliance with the inspection requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, New England Region, if the request contains substantiating data to justify that equivalent method for that operator. This supersedes Amendment 39-1992 (39 F.R. 37356), AD 74-22-02 and Amendment 39-2031 (39 F.R. 41739), AD 74-25-07. This amendment becomes effective June 12, 1975.
2012-23-06: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777 airplanes. This AD was prompted by reports of failure of wire support clamps in the forward section of the aft pressure bulkhead. This AD requires a detailed inspection of the clamps on the power feeder cable of the auxiliary power unit (APU) to determine if certain clamps are installed, and related investigative and corrective actions if necessary. We are issuing this AD to prevent failure of the clamp, which could result in wire chafing and potential arcing and consequent fire in section 48 (a flammable fluid leakage zone) or heat damage to the APU power feeder cable, insulation blankets, or pressure bulkhead.
2012-22-17: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-200 and -300 series airplanes. This AD was prompted by reports of cracks in the inner chords at both left-side and right-side stations 859.5, 883.5, and 903.5. This AD requires repetitive inspections of the frame inner chord transition radius for cracks, and related investigative and corrective actions if necessary. We are issuing this AD to prevent large cracks in the frames and adjacent structure that can adversely affect the structural integrity of the airplane.
50-04-02: 50-04-02 SUPERIOR (Culver): Applies to All Model V, Serial V-3 Through V-357 and Model V2, Serial V2-503 Through V2-517 Not Previously Modified in Accordance With Superior Service Bulletin No. 18. Compliance required at the next 100-hour inspection but not later than February 1, 1951. The teeth of the final pinion, P/N 10528, in the gear reduction train of the landing gear retraction motor have inadequate strength to sustain the shock loads due to abrupt reversal of the landing gear retraction switch and to maladjusted limit switches. As stripping of these teeth makes the emergency extension system inoperative, gears 10528 and 10529 should be replaced with gears 11520 and 11521 which have stronger teeth and are obtainable from the Superior Aircraft Co., University Airport, 2501 North Hillside, Wichita 25, Kansas. (Superior Service Bulletin No. 18 dated November 19, 1947, covers this same subject.) This supersedes AD 48-05-02, and eliminates placard installation provisions.
2012-23-04: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 737-100 and -200 series airplanes. The existing AD currently requires various inspections for cracks in the outboard chord of the frame at body station (BS) 727 and in the outboard chord of stringer (S) 18A, and repair or replacement of cracked parts. This new AD adds airplanes to the applicability statement in the existing AD and adds inspections for cracks in the BS 727 frame outboard chords and the radius of the auxiliary chord, for certain airplanes. This new AD also removes the inspections of the outboard chord of S-18A required by the existing AD. This AD was prompted by several reports of fatigue cracking in the frame outboard chord at BS 727 and in the radius of the auxiliary chord on airplanes that were not affected by the existing AD. We are issuing this AD to detect and correct fatigue cracking of the outboard and auxiliary chords, which could result in reduced structural integrity of the outboard chord and consequent rapid decompression of the airplane.
99-20-08: This amendment adopts a new airworthiness directive (AD), applicable to all McDonnell Douglas Model MD-11 series airplanes. This action prohibits installation of a certain In-flight Entertainment Network system. This amendment is prompted by the results of a special certification review of the in-flight entertainment system installed on a Model MD-11 series airplane that was involved in a recent accident. The actions specified in this AD are intended to prevent possible confusion as the flightcrew performs their duties in response to a smoke/fumes emergency, which could impair their ability to correctly identify the source of the smoke/fumes and subsequently affect the continued safe flight and landing of the airplane.