Results
2000-06-05: This amendment adopts a new airworthiness directive (AD) applicable to Eurocopter France Model SA330F, SA330G, SA330J, AS332C, AS332L, AS332L1, and AS332L2 helicopters. This action requires replacing certain tail rotor blades before further flight after April 30, 2000. This amendment is prompted by loss of control of a helicopter due to a lightning strike on a tail rotor blade. This condition, if not corrected, could result in loss of a tail rotor blade and subsequent loss of control of the helicopter
2009-18-06: 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: During operation in icing conditions, an asymmetric configuration of the de-icing boots was detected, occurring during the inflation and deflation check of the de-icing system. This was found to be due to an unexpected failure mode in the pneumatic and de-icing system's control electronic logic. This condition, if not corrected, could affect the de-icing capabilities of the boots installed on the wing and horizontal stabilizers, potentially leading to loss of control of the aircraft. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
72-21-05: 72-21-05 CANADAIR: Amendment 39-1536. Applies to all Canadair CL-44 type aircraft certificated in all categories. Compliance required as indicated. Within the next 100 hours in service after the effective date of this Airworthiness Directive, unless already accomplished within the last 1900 hours in service and at intervals not exceeding 2000 hours in service from the last inspection accomplish the following: 1. Inspect the horizontal stabilizer rear spar to fuselage attachment fittings, P/N 44A45022A and B, for cracks in accordance with Paragraph 3.4 of Canadair Service Information Circular No. 379-CL44, dated 7 July 1971, or equivalent inspection approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Replace cracked parts before further flight with parts of the same part number or FAA-approved equivalent parts approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be performed. Upon request, with substantiating data submitted through an FAA maintenance inspector, the replacement intervals specified herein may be adjusted by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective October 17, 1972.
2006-13-10: We are adopting a new airworthiness directive (AD) that supersedes AD 92-07-05, which applies to certain Raytheon Aircraft Company (Raytheon) (formerly Beech) 65, 90, 99, and 100 series airplanes. AD 92-07-05 currently requires you to inspect the rudder trim tab for proper moisture drainage provisions, and if the correct drainage provisions do not exist, before further flight, modify the rudder trim tab. This AD results from receiving and evaluating new service information that requires the actions of AD 92-07-05 for the added serial numbers LJ-1281 through LJ-1732 for the Model C90A airplanes. This AD retains all the actions of AD 92-07-05 and adds serial numbers LJ-1281 through LJ-1732 for the Model C90A airplanes in the applicability section. We are issuing this AD to prevent water accumulation in the rudder trim tab, which could result in a change in the mass properties and possibly a lower flutter speed of the airplane. A lower airplane flutter speed could result in failure and loss of control of the airplane.
2006-13-08: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A330-200, A330-300, A340-200, and A340-300 series airplanes; and Model A340-541 and A340-642 airplanes. This AD requires an inspection for anti-fretting material contamination of the Halon filters and plumbing parts of the flow metering system (FMS) and flow metering compact unit (FMCU) in the lower deck cargo compartment (LDCC) and bulk crew rest compartment (BCRC), as applicable; other specified actions; and corrective actions if necessary. This AD results from a report that the FMS and FMCU of the fire extinguishing system may be blocked by anti-fretting material contamination. We are issuing this AD to prevent such anti-fretting material contamination, which could reduce the effectiveness of the fire extinguisher system to discharge fire extinguishing agents and to lower the concentration of Halon gas in the LDCC or BCRC in a timely manner. An ineffective fire extinguisher system in the event of afire could result in an uncontrollable fire in the LDCC or BCRC.
2018-14-03: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes; Model CL-600-2D15 (Regional Jet Series 705) airplanes; Model CL-600-2D24 (Regional Jet Series 900) airplanes; and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by reports indicating that corrosion was found on the main landing gear (MLG) retraction actuator brackets and their associated pins. This AD requires an inspection of the retraction actuator brackets, their associated pins and hardware, and the mating lugs on the MLG outer cylinder for any corrosion, and replacement if necessary. We are issuing this AD to address the unsafe condition on these products.
65-05-01: 65-05-01 AERO PRODUCTS: Amdt. 39-42 Part 39 Federal Register March 4, 1965. Applies to Model A6441FN-606 Propeller Blades with Serial Numbers 3999 or below. Compliance required as indicated. To detect propeller blade cracks and prevent blade failure, accomplish the following: (a) When propeller roughness is reported, aircraft shall not be flown, except for evaluation flight to determine cause of propeller roughness, until cause of roughness is corrected. Only essential persons shall be carried during an evaluation flight. (b) Except as provided in (c), inspect by X-ray the cuff area of blades in accordance with Aero Products Propeller Service Bulletin No. 82 dated October 15, 1959, or later FAA- approved revisions at the following times unless already accomplished: (1) X-ray blades which had 10,000 or more hours' time in service on January 6, 1965, within 120 hours' time in service after January 6, 1965. (2) X-ray blades which had 8,000 or more butless than 10,000 hours' time in service on January 6, 1965, within 180 hours' time in service after January 6, 1965. (3) X-ray blades which had less than 8,000 hours' time in service on January 6, 1965, prior to the accumulation of 8,180 hours' time in service. (c) The following blades are not required to be initially X-rayed as required by (b) - (1) Blades shipped from Allison or after December 23, 1964; (2) Blades which had 10,000 or more hours' time in service on January 6, 1965, that have been magnafluxed externally and internally in the A and B thrust member cavity by any overhaul facility within the last 250 hours' time in service before January 6, 1965; (3) Blades which had less than 10,000 hours' time in service on January 6, 1965, that have been magnafluxed externally and internally in the A and B thrust, member cavity by any overhaul facility within the last 750 hours' time in service before January 6, 1965; or (4) Blades which have been modified in accordance with (e). The repetitive inspections required by (d) for blades 0.150 inch thickness or greater must be accomplished until modified in accordance with (e)(3). (d) Repeat the X-ray inspection required by (b) for blades with thrust member minimum thickness in the "A" area at last overhaul of 0.150 inch or greater thickness at the following times until modified in accordance with (e): (1) X-ray blades which had 10,000 or more hours' time in service on January 6, 1965, at intervals not to exceed 250 hours' time in service. (2) X-ray blades which had 8,000 or more but less than 10,000 hours' time in service on January 6, 1965, at intervals not to exceed 750 hours' time in service until the blade has accumulated 10,000 hours' time in service. Thereafter, X-ray at intervals not to exceed 250 hours' time in service. (3) X-ray blades which had less than 8,000 hours' time in services on January 6, 1965, at intervals not to exceed 750 hours' time inservice. (e) Modify the cuff of blades to provide an inspection window in accordance with Allison Commercial Service Letter No. 167, dated February 12, 1965, or later FAA-approved revisions at the following times based on thrust member thickness in the "A" area at last overhaul unless already accomplished: (1) Modify blades 0.144 inch thickness or less within 100 hours' time in service after the effective date of this AD. (2) Modify blades 0.145 inch to 0.149 inch thickness within 250 hours' time in service after the effective date of this AD. (3) Modify blades 0.150 inch thickness or greater within 500 hours' time in service after the effective date of this AD. (f) Visually inspect the blade shank surface within the cuff window for cracks in accordance with Allison Commercial Service Letter No. 167 or later FAA-approved revisions at the time modification required by (e) is made, and thereafter at intervals not to exceed 25 hours' time in service. (g) Remove cracked blades from service and report immediately by telephone or telegram to the Chief, Engineering and Manufacturing Branch, FAA Central Region, Kansas City, Missouri. (h) Remove blades from service according to the following schedule based on thrust member minimum thickness in the "A" area at last overhaul: (1) Remove from service blades 0.144 inch thickness or less which had 10,000 or more hours' time in service on February 17, 1965; within 50 hours' time in service after February 17, 1965. (2) Remove from service blades 0.144 inch thickness or less which had less than 10,000 hours' time in service on February 17, 1965, prior to the accumulation of 10,050 hours' time in service. (3) Remove from service blades 0.145 inch to 0.149 inch thickness which had 12,000 or more hours' time in service on February 17, 1965, within 50 hours' time in service after February 17, 1965. (4) Remove from service blades 0.145 inch to 0.149 inch thickness which had less than 12,000 hours' time in service on February 17, 1965, prior to the accumulation of 12,050 hours' time in service. (i) Upon the request of the operator, an FAA maintenance inspector, subject to the prior approval of the Chief, Engineering and Manufacturing Branch, FAA Central Region, may adjust the repetitive intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for such operator. NOTE. - "A" area is identified in Allison-Aero-products Overhaul Manual, Section 63-6- 0, Pages 315 and 316. This supersedes AD 65-01-01. This directive effective March 4, 1965.
51-21-02: 51-21-02 PIPER: Applies to All Model PA-12 Airplanes. Compliance required not later than October 15, 1951, and each 100 hours of operation thereafter unless reinforcements are installed. Carefully inspect aileron hinge brackets to false spar attachment fittings, P/N N10931, (3 per wing), for cracks at the bend between the channel and flat portions of the fittings. If cracked fittings are found, add reinforcement bracket P/N 12047. With reinforcement brackets P/N 12047 installed, special inspections may be discontinued. (Piper Service Bulletin No. 107, dated September 24, 1948, covers this same subject.)
68-17-03R1: We are adopting a new airworthiness directive (AD) to revise AD 68-17-03, which applies to all Pilatus Aircraft Ltd. (Pilatus) PC-6 series airplanes. AD 68-17-03 requires you to repetitively inspect the rudder end rib for cracks and replace the rudder end rib with a modified rudder end rib when you find cracks. Installing the modified rudder end rib terminates the repetitive inspection requirements of AD 68-17-03. Under a licensing agreement with Pilatus, Fairchild Republic Company (also identified as Fairchild Industries, Fairchild Heli Porter, or Fairchild-Hiller Corporation) produced Model PC-6 series airplanes (manufacturer serial numbers 2001 through 2092) in the United States. AD 68-17-03 was intended to apply to all affected serial numbers of Model PC-6 series airplanes listed on Type Certificate Data Sheet (TCDS) No. 7A15, including the Fairchild-produced airplanes. Consequently, this AD clarifies that all models of the PC-6 airplane on TCDS No. 7A15 (including those models produced under the licensing agreement by Fairchild Republic Company) are included in the applicability. We are issuing this AD to detect and correct cracks in the rudder end rib, which could result in failure of the rudder end rib. This failure could result in loss of rudder control.
2006-13-02: The FAA is adopting a new airworthiness directive (AD) for certain EMBRAER Model ERJ 170 airplanes. This AD requires inspecting for excess sealant applied to the attachment bolts of the negative pressure relief valve, and performing corrective actions if necessary. This AD results from reports that excess sealant was applied to the attachment bolts of the negative pressure relief valve, which interfered with the valve's movable diaphragm. We are issuing this AD to prevent incorrect operation of the negative pressure relief valve, which could result in negative pressures that exceed the structural strength limits of the airframe and lead to reduced structural integrity of the airplane.