Results
2015-23-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-200 Freighter, and A330-300 series airplanes; and Model A340-200 and A340-300 series airplanes. This AD was prompted by reports of cracked support strut body ends at a certain frame location of the trimmable horizontal stabilizer (THS). This AD requires repetitive inspections for cracking of the strut ends of the THS support located at a certain frame in the tail cone, and replacement if necessary; and reinstallation or installation of reinforcing clamps on certain strut ends. We are issuing this AD to detect and correct cracked support strut body ends of the THS, which could lead to the loss of all four THS support struts, making the remaining structure unable to carry limit loads, resulting in the loss of the horizontal tail plane.
2010-20-19: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Two cases of a crack on a "dry'' ADG [air driven generator] (Hamilton Sundstrand part number in the 761339 series), in the aft area of the strut and generator housing assembly, have been reported on CL-600-2B19 aircraft. The same part is also installed on CL-600- 2C10, -2D15 and -2D24 aircraft. Investigation determined that the crack was in an area of the strut where the wall thickness of the casting was below specification, due to a manufacturing anomaly in a specific batch of ADGs. Structural failure and departure of the ADG during deployment could possibly result in damage to the aircraft structure. If deployment was activated by a dual engine shutdown, ADG structural failure would also result in loss of hydraulics for the flight controls. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
2000-18-12: This amendment adopts a new airworthiness directive (AD) that applies to all Polskie Zaklady Lotnicze Spolka zo.o. (PZL-Mielac) Models PZL M18, PZL M18A, and PZL M18B airplanes. This AD requires you to repetitively inspect the centerwing-to-outboard wing attach joints for cracks in the lugs, corrosion in the main holes, and ovalization of the main holes; repair corrosion and apply anti-corrosion protection; replace the wing attach joints, as necessary; and eliminate any ovalization of the wing main joint holes. This AD is the result two instances of in-flight wing separation on Model PZL M18A airplanes where severe corrosion and pitting led to high stress concentrations on the wing attachment joints. The actions specified by this AD are intended to detect and correct cracks in the lugs, corrosion in the main holes, and ovalization of the main holes, in the centerwing-to-outboard wing attach joints. Such damage could result in failure of the joints with consequent in-flight wing separation.
2000-18-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Israel Aircraft Industries, Ltd., Model 1125 Westwind Astra series airplanes. This action requires revising the Airplane Flight Manual to provide the flight crew with operational guidance under certain failure conditions and a limitation not to engage the long-range navigation system during takeoff, approach, or landing. This action is necessary to prevent the loss of primary attitude and directional gyros, which relate position information to the flight crew. This action is intended to address the identified unsafe condition.
2015-23-10: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-8 series airplanes. This AD was prompted by a report of improperly installed outboard stowage bin modules in the passenger compartment found during maintenance. Further investigation revealed that certain attachment bracket bushings were missing or had moved out of the holes. This AD requires installing a spacer on the end of each quick-release pin that attaches the outboard stowage bin module to the lateral support tie rods of the main deck passenger compartment. We are issuing this AD to prevent detachment of the quick-release pin, which could result in separation of the lateral support tie rod and subsequent detachment of the module and consequent injuries to passengers or flightcrew.
2000-18-08: This amendment adopts a new airworthiness directive (AD) for MD Helicopters, Inc. (MDHI) Model MD-900 helicopters that requires modifying the non-rotating swashplate assembly and re-identifying it and the swashplate assembly with new part numbers. This AD also requires creating a component history card or equivalent record to track the life of the newly identified non-rotating swashplate assembly and establishing a life limit of 1800 hours time-in-service (TIS). Additionally, this AD requires inspecting and modifying, if necessary, the longitudinal drive link assembly. This AD is prompted by reports of damage to the longitudinal drive link assembly caused by the sharp inner edge of the bushing in the non-rotating swashplate assembly. The actions specified by this AD are intended to prevent damage to the longitudinal drive link, loss of control of the main rotor system, and subsequent loss of control of the helicopter.
92-23-05: 92-23-05 AIRBUS INDUSTRIE: Amendment 39-8405. Docket No. 91-NM-244-AD. Supersedes AD 90-14-05, Amendment 39-6648. Applicability: Model A300 series airplanes equipped with General Electric engines; up to and including airplane serial number 153 and serial number 157; on which Airbus Industrie Modification 8430 has not been installed; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To ensure proper operation of the fire extinguishing system, accomplish the following: (a) Within 400 hours time-in-service after July 23, 1990 (the effective date of Amendment 39-6648, AD 90-14-05), perform an inspection of the engine fire extinguishing pipe in the pylon area at rib 12, in accordance with Airbus Industrie All Operators Telex (AOT) 26/90/01, dated February 9, 1990, and Correction, dated February 9, 1990. If chafing is found, prior to further flight, repair in accordance with the AOT. (b) If no evidence of chafing is found as a result of the inspection required by paragraph (a) of this AD, perform repetitive visual inspections of the engine fire extinguishing pipe in the pylon area at rib 12 at intervals not to exceed 8,000 hours time-in-service, in accordance with Airbus Industrie Service Bulletin A300-26-055, Revision 1, dated September 4, 1991, or Revision 2, dated December 18, 1991. If wear is found that exceeds 0.6 mm (0.023 inch), prior to further flight, repair or replace the worn pipe in accordance with the service bulletin. (c) Within 18 months after the effective date of this AD, modify the engine fire extinguishing pipe, and test the fire extinguishing bottles, in accordance with Airbus Industrie Service Bulletin A300-26-055, Revision 1, dated September 4, 1991, or Revision 2, dated December 18, 1991. (d) Modification of the engine fire extinguishing pipe, in accordance with Airbus Industrie Service Bulletin A300-26-055, Revision 1, dated September 4, 1991, or Revision 2, dated December 18, 1991, constitutes terminating action for the repetitive visual inspections required by paragraph (b) of this AD. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (f) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The inspections, repair, replacement, modification, and test shall be done in accordance with the following Airbus Industrie service bulletins, as applicable, which contain the specified effective pages: Service Bulletin Referenced and Date Page Number Revision Level Shown on Page Date Shown on Page All Operators Telex (AOT) 26/90/01, February 9, 1990 1-2 (Original) February 9, 1990 Correction to All Operators Telex (AOT) 26/90/01, February 9, 1990 1 (Original) February 9, 1990 A300-26-055, Revision 1, September 4, 1991 1-22 1 September 4, 1991 A300-26-055, Revision 2, December 18, 1991 1, 5-6, 8-28 2-4, 7 2 1 December 18, 1991 September 4, 1991 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on December 14, 1992.
91-13-02: 91-13-02 AIRBUS INDUSTRIE: Amendment 39-7033. Docket No. 90-NM-227-AD. Applicability: Model A310-200 series airplanes, serial numbers 162 through 378, inclusive; on which Modification 4942 has not been incorporated (reference Airbus Industrie Service Bulletin A310-53-2013, Revision 1, dated April 17, 1986); certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage, accomplish the following: A. Prior to the accumulation of 12,000 landings, or within 6 months after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 landings, perform a visual inspection of the cabin floor structure between Frame 40 and Frame 46, in accordance with Airbus Industrie Service Bulletin A310-53-2056, dated April 18, 1990. B. If cracks are found, prior to further flight, replace the affected part or modify the corresponding area in accordance with Airbus Industrie Service Bulletin A310-53-2013, Revision 1, dated April 17, 1986. The modified area no longer needs to be inspected in accordance with paragraph A. of this AD. Unmodified areas must be inspected at intervals not to exceed 3,000 landings. C. Modification of the cabin floor structure between Frame 40 and Frame 46, in accordance with Airbus Industrie Service Bulletin A310-53-2013, Revision 1, dated April 17, 1986, constitutes terminating action for the repetitive visual inspections required by paragraphs A. and B. of this AD. D. An 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. E. Special 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-7033, AD 91-13-02) becomes effective on July 15, 1991.
2015-16-07 R1: We are adopting a new airworthiness directive (AD) for REIMS AVIATION S.A. Model F406 airplanes. This AD revises AD 2015-16-07, which required inspection of the left-hand and right-hand rudder control pedal torque tubes, and, depending on findings, replacement with a serviceable part. This AD retains the actions of AD 2015-16-07 and adds additional acceptable serviceable replacement parts. The AD was prompted by reports of detachment of the pilot's rudder control pedal in flight. We are issuing this AD to require actions to address the unsafe condition on these products.
76-10-04: 76-10-04 START & FLUG: Amendment 39-2612. Applies to H101 "Salto" gliders, certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent possible failure of the cockpit canopy locking device and the consequent inability of the pilot to use his parachute, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, either (1) Install an operating limitations placard on the instrument panel in full view of the pilot to read as follows: "ACROBATIC MANEUVERS PROHIBITED;" or (2) Modify the cockpit canopy fastening mechanism by installing polyamide stop blocks on both canopy fastening mechanisms in accordance with Start & Flug GmbH Technical Note No. 101-8, dated May 1, 1974 and Drawing No. 101-14-34, undated, or FAA-approved equivalents. (b) The placard specified in paragraph (a)(1) of this AD, if installed, may be removed upon the incorporation of the modification described in paragraph (a)(2) of this AD. This amendment becomes effective May 27, 1976.