Results
2022-27-09: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Helicopters Model EC130T2 helicopters. This AD was prompted by a crack in the tailboom. This AD requires repetitively inspecting the vibration level on the tail rotor drive shaft and, depending on the results, taking corrective action. This AD also requires reporting information and prohibits installing certain rotor drive shafts unless the inspection is done, as 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.
2010-24-03: This amendment adopts a new airworthiness directive (AD) for Robinson Model R22, R22 Alpha, R22 Beta, and R22 Mariner helicopters, and Model R44 and R44 II helicopters. This AD requires visually inspecting each tail rotor (T/R) control pedal bearing block support (support) for a crack, measuring the thickness of each support, installing support safety tabs on certain supports, and replacing supports of a certain thickness during the next 2,200 hour overhaul. This amendment is prompted by two reports of Model R22 helicopters experiencing broken supports during flight, which resulted in the T/R control pedals becoming jammed. The actions specified by this AD are intended to prevent the supports from breaking, which can bind the T/R control pedals, resulting in a reduction of yaw control and subsequent loss of control of the helicopter.
2001-17-09 R1: This amendment rescinds Airworthiness Directive (AD) 2000-17-09, which is applicable to certain McDonnell Douglas Model MD-11 series airplanes. That AD requires an inspection of the upper avionics circuit breaker panel at the main observer's station to detect damage of the wires and to verify the correct routing of the wire bundles; corrective actions, if necessary; and installation of a new clamp, spacer, and sta-straps. The requirements of that AD were intended to prevent chafing in the upper avionics circuit breaker panel of the main observer's station, which could result in arcing and consequent smoke and/or fire in the cockpit. Since the issuance of that AD, the FAA has determined that the improper procedures specified by the service bulletin referenced in that AD could lead to wiring pre-load conditions and consequent wire damage, and arcing in the upper avionics circuit breaker panel. Such conditions could result in arcing and consequent smoke and/or fire in the cockpit.
2001-19-02: This amendment adopts a new airworthiness directive (AD) that is applicable to GE CF34-3A1, -3B, and -3B1 turbofan engines with scavenge screens part numbers (P/N's) 4047T95P01 and 5054T86G02 installed in the B-sump oil scavenge system. This action requires initial and repetitive visual inspections and cleaning of the B-sump scavenge screens. This amendment is prompted by five reports of B-sump oil scavenge system failure causing engine in-flight shutdowns. The actions specified in this AD are intended to prevent B-sump scavenge screen blockage due to coking, which could result in ignition of B-sump oil in the secondary air system, fan drive shaft separation, and uncontained engine failure.
2017-04-15: We are adopting a new airworthiness directive (AD) for certain Learjet Inc. Model 36A airplanes. This AD was prompted by a report indicating that an aileron cable failed on an airplane during a tension check and a determination that Model 36A airplanes were not included in AD 2005-13-36, which addresses this issue for other Learjet Inc. airplanes. This AD requires a one-time inspection of the center ball of the aileron control cables for a defective swage, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
2001-18-13: This amendment adopts a new airworthiness directive (AD) for Eurocopter Deutschland GmbH (Eurocopter) Model EC135 P1 and EC135 T1 helicopters. This action requires, before further flight, adding a copy of this AD or a statement to the Emergency Procedures section of the Rotorcraft Flight Manual (RFM) to inform the pilot to reduce power and land as soon as practicable if a thump-like sound followed by unusual vibration occurs during flight. This action also requires visually inspecting for a crack or a break in certain main rotor drive torque strut (strut) assemblies at specified time intervals and recording details of the inspections in the historical or equivalent record. This AD also requires re-marking and relocating the strut as appropriate and replacing any unairworthy strut assembly with an airworthy strut assembly before further flight. Also, this AD establishes a life limit of 1000 hours time-in-service (TIS) for certain struts with an additional 1000 hours TIS for struts re-marked right-hand (RH) or left-hand (LH) before installing in the new location. This amendment is prompted by a report of a thump-like sound heard during flight followed by unusual vibrations due to failure of the RH strut between the main transmission and the fuselage. The actions specified in this AD are intended to prevent failure of a strut, failure of a worn or ineffective back-up emergency stop, and subsequent loss of control of the helicopter.
82-03-04 R1: 82-03-04 R1 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-4310 as amended by Amendment 39-4810. Applies to Lockheed Model L-1011-385 series airplanes, prior to Serial No. 1239, certificated in all categories. Compliance required as indicated, unless previously accomplished. A. To detect leakage of flammable fluids in areas from which fluids or vapors could reach the auxiliary power unit exhaust shroud, accomplish the following: 1. Within 400 hours time in service from the effective date of this AD, and at repetitive intervals not to exceed 400 hours time in service thereafter, perform leak tests and visual inspections as specified in the Accomplishment Instructions of Lockheed Service Bulletin 093-49- 058 dated July 31, 1981, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region. 2. If fuel or hydraulic fluid leakage is detected, repair or replace defective parts or components with serviceable units beforefurther flight. 3. Upon request of an operator, an FAA maintenance inspector, subject to prior approval by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of that operator if the request contains substantiating data to justify the change for that operator. B. To reduce the APU exhaust shroud skin temperature to a safe level, within 5000 flight hours or two (2) calendar years after the effective date of this amendment, whichever occurs first, install the APU Exhaust Duct and Shroud Insulation as specified in Part II, Accomplishment Instructions of Lockheed L-1011 Service Bulletin 093-49-058, Revision 3, dated October 28, 1982, or later revisions approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. This action terminates the requirements for repetitive inspections required by paragraph A., above. C. Alternate means of compliance with this AD, which provide an equivalent level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA Northwest Mountain Region. D. 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 required by this AD. All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to: Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Support Contracts, Dept. 63-11, U-33, B-1. These documents also may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington 98168, or 4344 Donald Douglas Drive, Long Beach, California 90808. Amendment 39-4310 became effective March 11, 1982. his Amendment 39-4810 becomes effective March 19,1984.
88-05-01 R1: 88-05-01 R1 SIKORSKY AIRCRAFT: Amendment 39-5856 as revised by Amendment 39- 6637. Docket No. 88-ASW-4. Applicability: Sikorsky Aircraft Model S-76B helicopters, Serial Numbers (S/N) 760312, 760314, 760316, 760317, 760318, 760319, 760327, 760330, 760331, and 760337, certificated in any category, equipped with the original cross beam cap angle, Part Number (P/N) 76070-20526-102, and the original cross beam web, P/N 76070-20526-139, -149, or -158. Compliance: For helicopters with 300 or more hours' time in service, compliance is required within the next 50 hours' time in service after the effective date of this amended AD, and thereafter at intervals not to exceed 50 hours' time in service from the last inspection. To prevent failure of the helicopter forward engine support cross beam, accomplish the following: (a) Visually inspect the forward engine support cross beam cap angle and web as follows: NOTE: The forward engine support cross beam is accessedby opening the engine air inlet/bypass cowl per Sikorsky Supplemental Maintenance Manual SA4047-76B-2, Section 53- 20-03. The cross beam is located towards the rear of the inlet area opening and extends across the fuselage. The beam is attached to the engine compartment deck and the engine forward mount fittings are attached to the cross beam upper cap angle. If the cross beam cannot be inspected properly from the inlet area because of interference with existing components, remove the main transmission drain access panels in the baggage compartment overhead. (1) Clean the forward surface of the cross beam as much as possible with dry cleaning solvent P-D-680, Type II, or equivalent. (2) Visually inspect, using a flashlight and mirror as necessary, the forward side of the upper cross beam cap angle and web for evidence of cracks. NOTE: Particular attention should be directed to areas under the inboard engine support fittings. (b) If cracks are detected visually, verify cracks by using a dye penetrant or equivalent inspection method. NOTE: Method Type II in MIL-STD-6866 is an acceptable inspection method. (1) If cracks are found in the cap angle, replace cracked part prior to further flight with a new part of the same part number. (2) If cracks are found in the web, prior to further flight, either replace the cracked part with a new part of the same part number or repair cracks found as a result of this AD with a method approved by the Manager, FAA, Boston Aircraft Certification Office. (c) Report cracks found, including location, length, fasteners and holes affected, replacement of parts, and total time in service on helicopter, by letter, to the Manager, Boston Aircraft Certification Office, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, within 10 days of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 2120-1156.) (d) Aircraft may be ferried in accordance with the provisions of the Federal Aviation Regulation (FAR) Sections 21.197 and 21.199 to a base where the AD can be accomplished. (e) Alternate inspections, repairs, modifications, or other means of compliance which provide an equivalent level of safety may be used if approved by the Manager, Boston Aircraft Certification Office, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, telephone (617) 273-7118. (f) Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Boston Aircraft Certification Office, may adjust the compliance time specified in this AD. This AD revises AD 88-05-01, Amendment 39-5856 (53 FR 5366, February 24, 1988). This amendment (39-6637, AD 88-05-01 R1) becomes effective on July 16, 1990.
2017-03-01: We are superseding airworthiness directive (AD) 2014-05-06 for Eurocopter Deutschland GmbH (ECD) (now Airbus Helicopters Deutschland GmbH) Model EC135 and MBB-BK 117 C-2 helicopters to correct an error in the compliance time. AD 2014-05-06 required inspecting the flight- control bearings and installing bushings and washers. This AD requires the same actions. These actions are intended to prevent an unsafe condition on these products.
2017-04-14: We are adopting a new airworthiness directive (AD) for certain Textron Aviation Inc. Model 560XL airplanes. This AD requires inspections of the fuel tube and right alternating current (AC) generator wires. This AD was prompted by reports of inadequate separation between the electrical wire bundle and fuel tube. We are issuing this AD to address the unsafe condition on these products.