Results
47-27-01: 47-27-01 WACO: (Was Mandatory Note 4 of AD-648-1.) Applies to Models UKS-7, VKS-7, VKS-7F Aircraft. Compliance required not later than next periodic inspection. Inspect tank area in wings for damage to plywood tank support and wing spars caused by collection of moisture in the boxed area of the fuel tank. 1. Remove the left and right fuel tanks and inspect the condition of the plywood tank support and the front and rear spars. 2. If the plywood supports are found to be in poor condition they should be replaced using new plywood. 3. If the spars have been affected by the accumulated moisture, repairs should be made in accordance with FAA requirements or in extreme cases the spar should be replaced. 4. In order to provide drainage of the tank compartment three holes 3/16 inch in diameter should be drilled through the plywood support at the extreme rear of the support as close to the rear spar as possible without damaging the spar. These drain holes should, of course, extend through the fabric covering. 5. The drain holes should be drilled in all tank compartments at the time the fuel tanks are removed for this inspection. (The above inspection and recommended remedial measures also covered by Waco Aircraft Co. Service Letter No. 3.)
47-06-04: 47-06-04 GLOBE: (Was Mandatory Note 7 of AD-766-5.) Applies to Models GC-1A and GC-1B Aircraft Serial Numbers 3 to 408 Inclusive; 1004 to 1224 Inclusive; and 2001 to 2324 Inclusive. Compliance required prior to April 1, 1947. Replace the AN 960-616 washers under the nuts at the attachment of the main landing gear retraction links to the shock struts with AN 940-616 washers. This is necessary for proper retention of the bushings in the retraction links. (Globe Customer Service Maintenance Bulletin No. 10 covers this same subject.)
2009-01-09: The FAA is superseding an existing airworthiness directive (AD) that applies to all Airbus Model A310 series airplanes. That AD currently requires repetitive detailed inspections to detect cracks propagating from the fastener holes that attach the left- and right- hand pick-up angles at frame 40 to the wing lower skin and fuselage panel, and corrective actions if necessary. This new AD revises the intervals for accomplishing the repetitive detailed inspections and provides for an optional terminating modification for the repetitive inspections. This new AD also revises the applicability of the AD to remove certain airplanes. This AD results from mandatory continuing airworthiness information originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. We are issuing this AD to prevent reduced structural integrity of the airplane due to fatigue damage, and consequent cracking of the pick-up angles at frame 40.DATES: This AD is effective April 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 2, 2009. The Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD as of February 9, 2001 (66 FR 1031, January 5, 2001).
2016-04-15: We are adopting a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI), Model 369A, 369D, 369E, 369FF, 369HE, 369HM, 369HS, 500N, and 600N helicopters with a certain part-numbered main rotor blade attach pin (pin) installed. This AD requires ensuring the life limit of the pin as listed in the Airworthiness Limitations section of aircraft maintenance records and Instructions for Continued Airworthiness (ICA). If the hours time-in-service (TIS) of a pin is unknown, or if a pin has exceeded its life limit, this AD requires removing the affected pin from service. This AD was prompted by a report from an operator who purchased pins that did not have life limit documentation. These actions are intended to document the life limit to prevent a pin remaining in service beyond its fatigue life, which could result in failure of a pin, failure of a main rotor blade, and subsequent loss of control of the helicopter.
70-17-03: 70-17-03 HUGHES: Amdt. 39-1070. Applies to Model 269 Series helicopters certificated in all categories, which incorporate lead-lag and flapping hinge bolts, P/N HS 1446- 10-68, (only the lead-lag bolts are affected on Model 269C) with vendor identification BM (stylized) impression stamped on top of the bolt heads hereinafter referred to a BM bolts. Compliance required as indicated. To detect cracks in the BM bolts, P/N HS 1446-10-68, accomplish the following: Within 50 hours time in service after the effective date of this AD, unless already accomplished, remove all BM bolts in accordance with Hughes Handbook of Maintenance Instruction (BM bolts with the head dyed green or a white dot painted in the recessed head have been inspected and are not affected by this AD. The white dot was used in instances where the green dye application was not effective.) Perform a magnaflux inspection of the BM bolts for evidence of cracking. (a) Replace any BM bolt which shows evidence of cracking, with a serviceable bolt prior to further flight. Efface the part number of any cracked bolts sufficiently to prevent their inadvertent return to service. (b) Any BM bolt which shows no evidence of cracking may be returned to service after it has been identified with a white dot painted in the recessed head of the bolt. NOTE: (Hughes Service Information Notice No. N-78, dated July 31, 1970, pertains to the same subject.) This amendment becomes effective August 20, 1970.
75-19-05: 75-19-05 GENERAL ELECTRIC COMPANY: Amendment 39-2365. Applies General Electric Company Models CJ610-9 turbojet and CF700-2C, CF700-2D, and CF700-2D-2 turbofan engines which had the gearbox and accessory drive horizontal drive shaft P/N 37C301961P102 aligned with alignment tool P/N 2C5525 within the last 800 hours time in service as of the effective date of this AD. Compliance required within the next 100 hours time in service after the effective date of this AD, unless previously accomplished. To prevent possible accessory drive horizontal drive shaft failure, leading to complete loss of engine power, inspect the horizontal drive shaft for alignment and spline wear, in accordance with General Electric Service Bulletin No. (CJ610) A72-117 or (CF700) A72-130 or later FAA approved revision or an equivalent inspection method approved by the Chief, Engineering and Manufacturing Branch, New England Region, Federal Aviation Administration. Remove worn horizontal drive shafts and mating female splined components and replace with serviceable parts in accordance with General Electric Alert Service Bulletin No. (CJ610) A72-117 or (CF700) A72-130 or later FAA approved revision. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of Chief, Engineering and Manufacturing Branch, FAA New England Region, may adjust the compliance time specified in the AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. General Electric Company Service Bulletins identified in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these Service Bulletins from General Electric Company may receive copies upon request to General Electric Company, 1000 Western Avenue, Lynn, Massachusetts 01910. These documents may also be examinedat the New England Region, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA headquarters, 800 Independence Avenue S.W., Washington, D.C. A historical file on this AD, which includes the incorporated material in full, is maintained by the FAA at its headquarters in Washington, D.C., and at the New England Regional office in Burlington, Massachusetts. This amendment becomes effective September 26, 1975.
2024-25-51: The FAA is adopting a new airworthiness directive (AD) for all Airbus Helicopters Deutschland GmbH Model MBB-BK 117 C-2 helicopters. The FAA previously sent this AD as an emergency AD to all known U.S. owners and operators of these helicopters. This AD was prompted by a report of vibrations of the yaw axis during a hover taxi. This AD requires repetitively inspecting the bolted joint between the cardan- pivot joint assembly and the tail rotor actuator piston rod and, depending on the results, taking corrective action. This AD also prohibits installing certain tail rotor actuators unless its requirements are met. These actions are specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2003-16-17: This amendment adopts a new airworthiness directive (AD) that applies to certain Dornier Luftfahrt GMBH (Dornier) Models 228-100, 228-101, 228-200, 228-201, 228-202, and 228-212 airplanes that have electrical cabin/cockpit heater option P05 or option P09 installed. This AD requires you to modify the cockpit and cabin auxiliary heating wiring. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to correct problems with the current design of the heater wiring, which could result in failure of the auxiliary cabin heater. Such failure could lead to overheating and smoke in the cockpit.
47-16-01: 47-16-01 DOUGLAS: (Was Mandatory Note 16 AD-762-7.) Applies to C-54 and DC-4 Aircraft. \n\n\tTo be complied with not later than September 1, 1947. \n\n\tA.\tIn those aircraft having the ammeter shunts in the positive generator leads, install two circuit breakers or circuit breaker switches in each nacelle junction box and reconnect each ammeter lead through one of these circuit breakers. Any type or variety of 10-ampere circuit break may be used, with the exception of the automatic-reset type. \n\n\tB.\tInstall a circuit breaker or circuit breaker switch in the main junction box and connect in series with the voltmeter circuit wire PJ-34 at the (d.c.) buss. Any type or variety of 10-ampere circuit breaker may be used, with the exception of the automatic-reset type. The nonoverride variety of circuit breaker is preferable. \n\n\tC.\tInstall for Heinemann type AM 1614-15-28-2 or equivalent, 15-ampere circuit breaker switches or circuit breakers, at the regulator location, in the leads to the B terminal of the voltage regulators; wires PA-530, PA-531, PA-730, and PA-731. The usual thermal circuit breaker or fuse does not provide sufficient protection to meet the peculiar requirements of a protective device for a generator field circuit application. \n\n\tAdditional information on the foregoing changes are described by Douglas Drawing No. 4350951 entitled "Rework of Generator Field Lead and Volt-Ammeter Lead Circuit Protection". A Douglas Aircraft Service Bulletin on this subject is also being issued.
2003-02-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and -400D series airplanes, that requires repetitive inspections to detect discrepancies of the drip shield and supports located above the rudder pedal mechanisms; corrective action, if necessary; and eventual modification of the drip shield, which would terminate the repetitive inspections. The actions specified by this AD are intended to prevent unrestrained drip shields from interfering with the rudder pedal mechanism, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.