Results
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.