Results
2013-24-09: We are adopting a new airworthiness directive (AD) for certain EADS CASA (Type Certificate Previously Held by Construcciones Aeron[aacute]uticas, S.A.) Model C-212-CB, C-212-CC, C-212-CD, C-212- CE, and C-212-DF airplanes. This AD was prompted by a report of the propeller pitch control (PPC) lever becoming disconnected from the engine due to a missing bolt. This AD requires modifying the PPC lever attachment system. We are issuing this AD to prevent PPC shaft disconnection, which could lead to a loss of propeller pitch control, possibly resulting in uncommanded change to the engine power settings and consequent reduced controllability of the airplane.
2013-24-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-100, -200, -200C, -300, -400, -500, -600, -700, -700C, -800, and -900 series airplanes. This AD was prompted by a report that the seat track attachment of body station 520 flexible joint is structurally deficient in resisting a 9g forward emergency load condition in certain seating configurations. This AD requires replacing the pivot link assembly on certain seats, modifying the existing seat track link assembly fastener on certain seats, or replacing the seat track link assemblies on certain seats. Also, for certain airplanes, this AD requires installing a new seat track link assembly or modifying the seat track link assembly. For certain other airplanes, this AD requires inspecting, changing, or repairing the seat track link assembly. We are issuing this AD to prevent seat detachment in an emergency landing, which could cause injury to occupants of the passenger compartment and affectemergency egress.
2013-23-18: We are adopting a new airworthiness directive (AD) for certain General Electric Company (GE) GE90-110B1 and -115B turbofan engines. This AD was prompted by multiple events of a leaking variable bypass valve (VBV) actuator fuel supply tube. This AD requires replacement of this VBV actuator fuel supply tube with a part eligible for installation. We are issuing this AD to prevent failure of the affected fuel supply tube, fuel leakage, engine fire, and damage to the airplane.
2000-24-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, and Model A300-600 series airplanes, that requires repetitive inspections to detect chafing and the existence of repairs of the harness of the high-level sensor of the fuel surge tanks, and to detect chafe marks on the support canisters of the magnetic level indicators; and follow-on corrective actions, if necessary. This amendment also requires modification of the harness for the high-level sensor of the outer wing fuel tanks, which terminates certain repetitive inspections. 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 chafing of the harness of the high-level sensor, which could result in a short circuit and consequent fuel ignition source inside the outer wing fuel tanks.
75-08-02: 75-08-02 DE HAVILLAND: Amendment 39-2149. Applies to de Havilland Model DHC- 6 Series Twin Otter Aircraft, Serial Nos. 1 through 135 inclusive. Compliance required as indicated. To preclude the hazard created by the failure of the right hand aileron control cable through contact with DC electrical power cable coded 2P66A8, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this A.D., alter the attachment of terminal block TB-17 and the routing of the cable harness to terminal block TB-17 and TB-18 in accordance with de Havilland Service Bulletin No. 6/304, Revision B, dated June 28, 1974, or equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Upon request with substantiating data submitted through an FAA inspector, the compliance time specified in this A.D. may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment is effective April 7, 1975.
2013-24-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 707 airplanes; and Model 720 and 720B series airplanes. This AD was prompted by reports indicating that a standard access door was located where an impact-resistant access door was required, and stencils were missing from some impact-resistant access doors. This AD requires an inspection of the left- and right-hand wing fuel tank access doors to determine that impact-resistant access doors are installed in the correct locations, and to replace any door with an impact-resistant access door if necessary. This AD also requires an inspection for stencils and index markers on impact-resistant access doors, and application of new stencils or index markers if necessary. This AD also requires revising the maintenance program to incorporate changes to the airworthiness limitations section. We are issuing this AD to prevent foreign object penetration of the fuel tank, which could cause a fuel leak near an ignition source (e.g., hot brakes or engine exhaust nozzle), consequently leading to a fuel-fed fire.
2013-24-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. This AD was prompted by reports of fractured rudder pedal tubes installed on the pilot-side rudder bar assembly. This AD requires repetitive inspections for cracking and damage of both pilot-side rudder pedal tubes, and replacement of affected pilot-side rudder bar assemblies if necessary. We are issuing this AD to detect and correct cracking of both pilot-side rudder pedal tubes, which could result in loss of pilot rudder pedal input causing reduced yaw controllability or a runway excursion.
2000-02-28: This document adopts a new airworthiness directive (AD) that applies to all AeroSpace Technologies of Australia Pty Ltd. (AeroSpace Technologies) Models N22B and N24A airplanes. This AD requires you to revise the Airplane Flight Manual (AFM) to include requirements for activating the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews have the information necessary to activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. Without this information, flightcrews could experience reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle
71-24-02: 71-24-02 FAIRCHILD HILLER ROTORCRAFT: Amdt. 39-1334. Applies to Model 1100 and FH-1100 Type Helicopters certificated in all categories. Compliance required as indicated. To preclude fatigue failure of the transmission mount strut, P/N 24-28031, due to internal corrosion, accomplish the following: Within the next 30 days after the effective date of this AD, unless already accomplished replace P/N 24-28031 left side, lateral, adjustable transmission strut with P/N 24-28031-11 strut in accordance with Section 28 of the FH-1100 Service Manual or an alternate method approved by the Chief, Engineering & Manufacturing Branch, FAA, Eastern Region. Upon installation of MS-21252 fork fitting apply RTV-102 sealant or equivalent to the threads of fitting and under AN316-5R retaining nut. This amendment is effective November 24, 1971.
2018-07-15: We are adopting a new airworthiness directive (AD) for XtremeAir GmbH Model XA42 airplanes equipped with an engine mount part number XA42-7120-151. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and address an unsafe condition on an aviation product. The MCAI describes the unsafe condition as cracking of the diagonal strut of the engine mount frame. We are issuing this AD to require actions to address the unsafe condition on these products.
2013-24-08: We are superseding airworthiness directive (AD) 2006-06-14 for certain Airbus Model A318-100 and A319-100 series airplanes, A320-111 airplanes, A320-200 series airplanes, and A321-100 and A321-200 series airplanes. AD 2006-06-14 required operators to review the airplane's maintenance records to determine the part numbers of the magnetic fuel level indicators (MFLIs) of the wing fuel tanks, and perform related investigative and corrective actions if necessary. This new AD also requires an inspection (improved method) to determine the part numbers of the MFLIs, and, if necessary, replacement of the MFLI or repair. This AD was prompted by information that the related investigative actions of AD 2006-06-14 are not fully effective and that an affected MFLI could still be installed on airplanes on which the [[Page 71993]] related investigative actions were accomplished. We are issuing this AD to prevent an ignition source in the wing fuel tank in the event of a lightning strike, which could result in a fire or explosion.
2003-12-15: This amendment adopts a new airworthiness directive (AD), that is applicable to Rolls-Royce (RR) plc RB211-535E4-37, RB211-535E4-B-37, and RB211-535E4-B-75 series turbofan engines. This amendment requires introducing an alternative technique to ultrasonically inspect installed fan blades on-wing using a surface wave ultrasonic probe. This action also adds the application of Metco 58 blade root coating as an optional terminating action. This amendment is prompted by the discovery of cracks on LPC fan blade roots during an engine overhaul. The actions specified by this AD are intended to detect cracks in LPC fan blade roots, which if not detected, could lead to uncontained multiple fan blade failure, and damage to the airplane.
75-17-12: 75-17-12 SLINGSBY SAILPLANES: Amendment 39-2314. Applies to Slingsby T59D Kestrel gliders certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent dive brake retraction failure, accomplish the following: (a) Within the next 10 hours' time in service after the effective date of this AD, install a placard on the instrument panel in full view of the pilot reading: "AIR BRAKE EXTENSION LIMITATION FINAL APPROACH 50% FLAREOUT ON LANDING 100% CRUISE NONE (0%)" (b) Within the next 50 hours' time in service after the effective date of this AD, replace the dive brake control mechanism with the linear type dive brake control mechanism, P/N 59A-45-717, in accordance with Slingsby Sailplanes Technical Instruction No. 75 dated May 21, 1975, or an FAA approved equivalent. (c) The placard required by paragraph (a) of this AD may be removed after the work specified in paragraph (b) of this AD has been accomplished. This amendment becomes effective August 18, 1975.
2013-24-01: We are adopting a new airworthiness directive (AD) for The Boeing Company Model 747-8 and 747-8F series airplanes and Model 787-8 airplanes powered by GEnx engines. This AD requires revising the airplane flight manual to advise the flight crew of potential ice crystal icing (ICI) conditions at high altitudes, and to prohibit operation in moderate and severe ICI conditions. This AD also requires inspecting the engine after any ICI event is detected by the flight crew. This AD was prompted by reports of engine damage and thrust loss events as a result of flying in high altitude ICI conditions. We are issuing this AD to ensure that the flight crews have operating instructions to avoid flight into ICI conditions that can lead to engine damage and thrust loss events; unrecoverable thrust loss on multiple engines can lead to a forced landing.
2013-23-12: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 turbofan engines. This AD requires replacement or repair of the low-pressure (LP) compressor fan blade set before reaching a specified number of flight cycles since new (FCSN) or flight cycles since last leading edge profile blade repair (FCSLR). This AD was prompted by reports of erosion of the leading edge profile of the LP compressor blade set contributing to fan blade flutter. We are issuing this AD to prevent failure of the LP compressor blades, which could lead to an uncontained engine failure and damage to the airplane.
67-08-05: 67-08-05 FAIRCHILD-HILLER: Amdt. 39-365 Part 39 Federal Register March 11, 1967. Applies to Model F-27 Series Airplanes Incorporating Stewardess Seat Assembly, Fairchild Drawings No. 27-770633 and 27-770634. Compliance required within the next 50 hours' time in service after the effective date of this AD unless already accomplished. To prevent injury to occupants of stewardess seat assemblies, accomplish the following: (a) Conspicuously post in the vicinity of the stewardess seat and in full view of the seat occupant a placard reading as follows: "Do not occupy stewardess jump seat during take-off or landing." (b) The placard required in (a) may be removed when there has been incorporated into the seat assembly a modification approved by the Chief, Engineering and Manufacturing Branch, Eastern Region. This directive effective March 11, 1967.
77-17-04: 77-17-04 MOONEY: Amendment 39-3006 as amended by Amendment 39-3258. Applies to Models M20, M20A, M20B, M20C, M20D, M20E, M20F, and M20G airplanes, certificated in all categories with over 1000 hours' time in service. Compliance required within the next 30 days after the effective date of this AD, unless already accomplished within the last 250 hours' time in service and thereafter at intervals not to exceed 500 hours' time in service from the last inspection. To prevent failure of the control wheel shaft due to cracking with associated crack growth, accomplish the following: (a) Remove the RH and LH control wheels and inspect the aft two inches of the control wheel shaft for cracks (particularly at the attachment holes for the wheel). Use visual and dye penetrant inspection methods. (b) Replace or modify any cracked shafts with new original configuration shafts or with the strengthened configurations described in Mooney Service Bulletin M20-205B dated May 3, 1978, beforefurther flight. (c) Reinstall the RH and LH control wheels. (d) Replacement of parts required by paragraph (b) with new original configuration parts will permit the establishment of new initial inspection times for the inspections of paragraph (a). The new initial inspection time is 1,000 hours' time in service after parts replacement. Replacement or modification of parts required by paragraph (b) with the strengthened configurations described in Mooney Service Bulletin M20-205B will remove the requirement for the 500-hour repetitive inspections. (e) Aircraft may be flown in accordance with FAR 21.197 to a base where this AD can be accomplished. (f) The 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). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to the Service Manager, Mooney Aircraft Corporation, P.O. Box 72, Kerrville, Texas 78028. These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, 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 Southwest Regional Office in Fort Worth, Texas. (g) Equivalent methods of complying with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region. Amendment 39-3006 became effective August 18, 1977. This amendment 39-3258 becomes effective July 7, 1978.
2013-23-17: We are adopting a new airworthiness directive (AD) for Rolls- Royce plc (RR) RB211-535E4-37, -535E4-B-37, -535E4-C-37, RB211Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD requires removal of certain high-pressure (HP) and intermediate-pressure (IP) turbine discs before their accumulated cyclic lives have reached the revised limits. This AD was prompted by a report of an HP disc contaminated with a steel inclusion. We are issuing this AD to prevent failure of the HP or IP turbine disc, uncontained engine failure, and damage to the airplane.
2013-24-06: We are adopting a new airworthiness directive (AD) for all Thielert Aircraft Engines GmbH TAE 125-01 reciprocating engines. This AD requires applying sealant to close the engine clutch housing (crankcase assembly) opening. This AD was prompted by a report of engine power loss due to engine coolant contaminating the engine clutch. The design of the engine allows the crankcase assembly opening to be susceptible to contamination from external sources. We are issuing this AD to prevent in-flight engine power loss, which could result in loss of control of, and damage to, the airplane.
2013-23-15: We are superseding Airworthiness Directive (AD) 2009-06-02, which applied to certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747SR, and 747SP series airplanes. AD 2009-06-02 required repetitive inspections for skin cracks at the shear tie end fastener locations of the fuselage frames, and repair of cracks if necessary. This new AD also requires repetitive inspections for skin cracks next to the shear tie on airplanes with certain existing repair doublers, and corrective actions if necessary. This AD also revises the applicability to include additional airplanes. This AD was prompted by additional cracking found on an airplane not affected by AD 2009-06-02. We are issuing this AD to detect and correct fatigue cracks in the fuselage skin that can propagate and grow, and result in reduced structural integrity and sudden decompression of the airplane in flight.
78-18-02: 78-18-02 MCDONNELL DOUGLAS: Amendment 39-3289. Applies to Model DC-3 Series, DC-3A Series, DC-3C Series, DC-3D, Super DC-3 and R4D Series certificated in all categories, including all military models. \n\n\tCompliance required as indicated. \n\n\tTo minimize the possibility of a jammed elevator control system, due to cable interference accomplish the following: \n\n\t(a)\tWithin the next 25 hours time in service after the effective date of this AD; unless already accomplished within the last 60 days: \n\n\tNOTE: Determine that the elevator control system is properly rigged prior to accomplishment of the inspections required by this AD. \n\n\t\t(1)\tVisually inspect the right and left elevator upper cables and cable fittings for possible interference with the bulkhead frame and channel located just aft of the control column assembly at fuselage station (F.S.) 63 on the DC-3 Series and at F.S. 24 on the Super DC-3. The elevator cable and/or cable fitting must have 3/32 inch minimum clearance relative to the bottom of the cutout hole and both legs of the channel, throughout full cable travel. Pay particular attention to clearance when the elevator horn of the control column is rotated to the lowest point of its movement arc. \n\n\tNOTE: The channel is attached to aft side of bulkhead frame and the upper elevator cables are attached to extreme bottom of control column elevator horn, located forward of the bulkhead frame. Inspection may be accomplished after removal of external access plates on bottom of fuselage, forward and aft of F.S. 63 on DC-3 Series and F.S. 24 on the Super DC-3. \n\n\t\t(2)\tIf existing clearance is less than required by paragraph (a)(1), trim out the cable cutout hole in the bulkhead frame and both legs of the channel to provide a nominal clearance of 1/8 + 1/32 inches using a minimum 1/4 inch corner radius. Break and smooth all edges. \n\n\t(b)\tSpecial flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate airplanes to abase for accomplishment of the inspection required by paragraph (a)(1). \n\n\t(c)\tEquivalent modifications may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis amendment becomes effective September 6, 1978.
91-22-04: 91-22-04 BOEING: Amendment 39-8064. Docket No. 91-NM-105-AD. \n\n\tApplicability: Model 707/720 series airplanes with a main cargo door, listed in Boeing Service Bulletin 3477, dated July 26, 1990; and Models 727-100C and 727-200F series airplanes, listed in Boeing Service Bulletin 727-52-0142, dated July 26, 1990; certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished, or unless the main cargo door has been deactivated in accordance with Boeing Service Bulletin 3311, dated May 26, 1978 (for Model 707/720 series airplanes), or Boeing Service Bulletin 727-29-0053, dated July 8, 1977 (for Model 727 series airplanes). \n\n\tTo prevent inadvertent opening of the main cargo door, accomplish the following: \n\n\t(a)\tWithin the next 30 days after the effective date of this AD, change the operating procedures for the main cargo door to include the following requirements, and thereafter comply with those revised procedures until the inspection required by paragraph (b) of this AD has been accomplished: Prior to takeoff following each operation of the door, conduct a visual verification, through the external viewports, to ensure proper engagement of the latching cams to ensure that the door is fully latched closed. This information must be relayed to and acknowledged by the flight crew. \n\n\t\t(1)\tThe procedures required by this paragraph must be accomplished by a qualified and trained mechanic or flight officer, and the training program must be approved by the FAA Principal Maintenance Inspector (PMI). \n\n\t\t(2)\tDocumentation of compliance with these procedures is required and the method of documentation must be approved by the FAA PMI.\n \n\t(b)\tWithin the next 18 months after the effective date of this AD, perform a visual inspection for wear of the mating surfaces of the pressure relief door hinge fittings and latch cams of the main cargo door, in accordance with Section III, Part I, of the Boeing Service Bulletin 3477, dated July 26, 1990 (for Model 707/720 series airplanes), or Boeing Service Bulletin 727-52-0142, dated July 26, 1990 (for Model 727 series airplanes). \n\n\t\t(1)\tIf wear exceeds the limits specified in the applicable service bulletin: Prior to further flight, replace worn parts, as follows. Do not intermix original configuration parts with modified parts in the same door. \n\n\t\t\t(i)\tReplace worn parts with modified parts in accordance with Section III, Part II, of the applicable service bulletin; or \n\n\t\t\t(ii)\tReplace worn parts with airworthy parts of the original configuration in accordance with FAA-approved procedures. \n\n\t\t(2)\tThe inspection and replacement of parts, if necessary, in accordance with this paragraph constitutes terminating action for the special operating procedures required by paragraph (a) of this AD. \n\n\t(c)\tWithin 36 months after the effective date of this AD, accomplish the following in accordance with Section III, Part II, of Boeing Service Bulletin 3477, dated July 26, 1990 (for Model 707/720 series airplanes), or Boeing Service Bulletin 727-52-0142, dated July 26, 1990 (for Model 727 series airplanes). \n\n\t\t(1)\tReplace the latch cams, \n\n\t\t(2)\tReplace the latch cam bellcranks, \n\n\t\t(3)\tReplace the pressure relief door hinge fittings, and \n\n\t\t(4)\tPerform the operation, control, and door warning system tests. \n\n\t(d)\tFor airplanes on which the main cargo door has been deactivated: \n\n\t\t(1)\tPrior to reactivating the main cargo door, accomplish the inspection required by paragraph (b) of this AD. \n\n\t\t(2)\tWithin the next 18 months after reactivation, or within 36 months after the effective date of this AD, whichever is later, accomplish the requirements of paragraph (c) of this AD. \n\n\t(e)\tThe accomplishment of Section III, Part II, of Boeing Service Bulletin 3477, dated July 26, 1990 (for Model 707/720 series airplanes), or Boeing Service Bulletin 727-52-0142, dated July 26, 1990 (for Model 727 series airplanes), as applicable, constitutes terminating action for the requirements of this AD. \n\n\t(f)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(g)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\t(h)\tThe inspection and repair requirements shall be done in accordance with Boeing Service Bulletin 3477, dated July 26, 1990, or Boeing Service Bulletin 727-52-0142, dated July 26, 1990, as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Boeing Commercial Airplane Group, P.O. Box 3707, Seattle, Washington 98124. Copies may be inspected at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington; or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C. \n\n\tThis amendment (39-8064, AD 91-22-04) becomes effective on November 29, 1991.
2018-07-09: 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 a report of a smoke-in-cabin event due to a non-sustaining electrical fire. This AD requires installation of protective sleeves on the bonding jumper wires of affected galleys and lavatories. We are issuing this AD to address the unsafe condition on these products.
2013-23-13: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 series airplanes; Model A300 B4-600, B4-600R, and F4- 600R series airplanes; and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a report that cracking was found in area 2 of the frame base fittings between frame 41 and frame 46. This AD requires a check of maintenance records to determine if certain repairs were done in area 1 of the frame base fittings, and, for affected airplanes, a detailed inspection for cracking in area 2 of the frame base fittings between frame 41 and frame 46, and repair if necessary. We are issuing this AD to detect and correct cracking in area 2 of the frame base fittings between frame 41 and frame 46, which could adversely affect the structural integrity of the airplane.
2013-23-08: We are adopting a new airworthiness directive (AD) AQUILA-- Aviation by Excellence AG Model AT01 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as a defective sealing of a tapped through bore hole at the inside of the fuel tank openings in combination with prolonged periods at maximum fuel level. We are issuing this AD to require actions to address the unsafe condition on these products.