Results
98-11-32: This amendment adopts a new airworthiness directive (AD) that is applicable to Allison Engine Company AE 3007A and AE 3007C series turbofan engines. This action supersedes priority letter AD 98-02-09, that currently requires certain checks of the center sump magnetic chip collector plug for paste. Engines found with paste are required to be removed from service. This action references revisions of the applicable Alert Service Bulletins (ASB) providing clarifications of check procedures. This amendment is prompted by a change in the part number applicability, a change in the check interval, and the publication of these revised ASBs. The actions specified by this AD are intended to prevent No. 4 bearing failure due to excessive bearing wear, which can result in an inflight engine shutdown. DATES: Effective June 18, 1998 The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 18, 1998. Comments for inclusion in the Rules Docket must be received on or before August 3, 1998.
99-02-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330-301, -321, -322, -341, -342, and A340-211, -212, -213, -311, -312, and -313 series airplanes. This action requires repetitive high-frequency eddy current (HFEC) inspections to detect cracking of the inner flange of the rear fuselage frame FR73A, between beams 5 and 6; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct fatigue cracking of the inner flange of the rear fuselage frame FR73A, which could result in reduced structural integrity of the fuselage.
99-02-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320 and A321 series airplanes. This amendment requires modification of the slat and flap control computer (SFCC) in the aft electronics rack. 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 failure of the SFCC caused by computer software anomalies or contamination by conductive dust. This condition, if not corrected, could result in uncommanded slat retraction during takeoff and consequent insufficient wing lift available to complete a successful takeoff.
97-10-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A310 series airplanes, that requires repetitive inspections to detect discrepancies or damage of the steady bearing assemblies of the flap transmission system, and replacement of any discrepant or damaged assembly with a new, like assembly. This amendment also requires eventual replacement of all the steady bearing assemblies with new, improved assemblies, which terminates the repetitive inspection requirements. This amendment is prompted by reports of cracking of the hardened steel inner race, and broken or missing inner races of the steady bearing assemblies. The actions specified by this AD are intended to prevent such discrepancies and damage of the shafts of the steady bearing assemblies, which could cause the shafts to fail; failure of the steady bearing shafts during a subsequent asymmetric stop could result in an uncommanded asymmetric retraction of the flap, and subsequentreduced controllability of the airplane.
75-01-03: 75-01-03 ROCKWELL INTERNATIONAL: Amendment 39-2061. Applies to all NA- 265, NA-265-20, -30, -40, -60, -70 and -80 model airplanes, certificated in all categories. Compliance required as indicated. To provide temporary operating limitations on airplanes affected, pending modification of the landing gear warning system to ensure continuous functioning of the aural warning device under the conditions of CAR 4b, accomplish the following: (1) The following operating limitation is hereby adopted effective ten days after the effective date of this AD, applicable to NA-265-60, -70 and -80 model airplanes: "MAXIMUM TAKEOFF AND LANDING PRESSURE ALTITUDE - 8,000 FEET." (2) For NA-265-60, -70 and -80 model airplanes, within ten days after the effective date of this AD, unless already accomplished, install a placard: "MAXIMUM TAKEOFF AND LANDING PRESSURE ALTITUDE - 8,000 FEET. GEAR WARNING HORN MAY NOT SOUND ABOVE 125 KIAS WITH FLAPS LESS THAN 80%." (3) For NA-265, NA-265-20, -30 and -40 model airplanes, within ten days after the effective date of this AD, unless already accomplished, install a placard: "GEAR WARNING HORN MAY NOT SOUND ABOVE 125 KIAS WITH FLAPS LESS THAN 80%." (4) Within 9 months after the effective date of this AD, unless already accomplished, remove and replace the altitude and airspeed switch, in accordance with Rockwell International Sabreliner Service Bulletin 74-32, dated December 18, 1974, or later FAA-approved revisions. (5) Equivalent installations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiating data. (6) After accomplishing the work required by paragraph 4, above, or FAA-approved equivalent per paragraph 5, the operating limitation imposed by paragraph 1, above, will no longer apply and the placards specified in paragraphs 2 and 3, above, must be removed. (7) Airplanes may be flown to a base for accomplishment of the installation required by paragraph 4, above, per FAR's 21.197 and 21.199. This amendment becomes effective January 6, 1975.
2021-25-13: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model CL-600-1A11 (600), CL-600-2A12 (601), and CL-600-2B16 (601-3A, 601-3R, and 604 Variants) airplanes. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. The FAA is issuing this AD to address the unsafe condition on these products.
98-03-11: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300, A310, and A300-600 series airplanes. For certain airplanes, this amendment requires replacing the bearings of the throttle control levers with new sealed bearings. For certain other airplanes, this amendment requires replacing the throttle control assemblies with new assemblies. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent asymmetric engine thrust on the airplane when the autothrottle is engaged, which could result in roll and yaw disturbances, and consequent reduced controllability of the airplane.
2021-24-14: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by reports of damage to the thrust reverser (TR) translating sleeve secondary sliders due to contact between the slider and the slider track liner. This damage could reduce the fatigue life of the slider below its full design life for the TRs installed on certain engines. This AD requires determining the serial number of the TR and performing applicable on-condition actions; or replacing the TR with a serviceable TR. The FAA is issuing this AD to address the unsafe condition on these products.
89-10-11 R1: 89-10-11 R1 BELL HELICOPTER TEXTRON, INC.: Amendment 39-6211 as corrected by Amendment 39-6283. (Airworthiness Docket No. 88-ASW-55) Applicability: Bell Helicopter Textron, Inc., Model 206A and 206B helicopters certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent possible in-flight engine flameout, which could result in the loss of the helicopter, accomplish the following: (a) Within the next 20 days after the effective date of this AD, revise the following Rotorcraft Flight Manual and Rotorcraft Flight Manual Supplements, as applicable. (1) For Model 206A helicopters, revise the FAA approved Rotorcraft Flight Manual (RFM) No. BHT-206A-FM-1 Operating Limitations, Section 1, Type of Operation, by adding the following: The following equipment shall be installed when conducting flight operations in falling and/or blowing snow to prevent possibility of engine flameout: The Particle Separator Engine Air Induction System Kit and the Deflector Kit. (See BHT-206A-FMS-18 and BHT-206A-FMS-24.) or The Snow Winterization Air Induction System. (See BHT-206A-FMS- 11.) (2) For Model 206A helicopters, revise the FAA approved Rotorcraft Flight Manual Supplement (RFMS) Nos. BHT-206A-FMS-18 and BHT-206A-FMS-24 Operating Limitations, Section 1, Type of Operation, by adding the following: The FAA approved Engine Air Induction Deflector Kit No. 206-706-136 shall be installed in conjunction with the Particle Separator Air Inducting Kit No. 206-706-201-17 or 206-706-200-9 when conducting flight operations in falling and/or blowing snow, and the following limits apply: Hover flight in falling and/or blowing snow is limited to a 20-minute duration after which the helicopter must be landed and checked for snow and/or ice accumulation. Flight operations are prohibited when visibility in falling and/or blowing snow is less than one- half (1/2) statute mile. (3) For Model 206B (206B II) helicopters, revise the FAA approved RFM No. BHT-206B-FM-1 Operating Limitations, Section 1, Type of Operation, by adding the following: The following equipment shall be installed when conducting flight operations in falling and/or blowing snow to prevent possibility of engine flameout: The Particle Separator Engine Air Induction System Kit and The Deflector Kit. (See BHT-206B-FMS-15 and BHT-206B-FMS-18.) (4) For Model 206B (206B II) helicopters, revise FAA approved RFMS Nos. BHT-206B-FMS-15 and BHT-206B-FMS-18 Operating Limitations, Section 1, Type of Operation, by adding the following: The FAA approved Engine Air Induction Deflector Kit No. 206-706-136 shall be installed in conjunction with the Particle Separator Air Induction Kit No. 206-706-200-5 or 206-706-201-11 when conducting flight operations in falling and/or blowing snow, and the following limits apply: Hover flight in falling and/or blowing snow is limited to a 20-minute duration after which the helicopter must be landed and checked for snow and/or ice accumulation. Flight operations are prohibited when visibility in falling and/or blowing snow is less than one- half (1/2) statute mile. (5) For Model 206B (206B III) helicopters, revise the FAA approved RFM No. BHT-206B3-FM-1 Operating Limitations, Section 1, Type of Operation, by adding the following: The following equipment shall be installed when conducting flight operations in falling and/or blowing snow to prevent possibility of engine flameout: The Particle Separator Engine Air Induction System Kit and the Deflector Kit. (See BHT-206B3-FMS-10 and BHT-206B3-FMS-12.) (6) For Model 206B (206B III) helicopters, revise the FAA approved RFM Nos. BHT-206B3-FMS-10 and BHT-206B3-FMS-12 Operating Limitations, Section 1, Type of Operation, by adding the following: The FAA approved Engine Air Induction Deflector Kit No. 206-706-136 shall be installed in conjunctionwith the Particle Separator Air Induction Kit No. 206-706-201 or 206-706-200 when conducting flight operations in falling and/or blowing snow, and the following limits apply: Hover flight in falling and/or blowing snow is limited to a 20-minute duration after which the helicopter must be landed and checked for snow and/or ice accumulation. Flight operations are prohibited when visibility in falling and/or blowing snow is less than one- half (1/2) statute mile. (b) Adding the following RFM and RFMS revisions to the basic RFM manual, as applicable, is an approved alternate method of compliance with paragraph (a) of this AD: BHT-206A-FM-1, Rev. D-39 BHT-206A-FMS-18, Rev. 6 BHT-206A-FMS-24, Rev. 3 BHT-206B-FM-1, Rev. B-39 BHT-206B-FMS-15, Rev. 4 BHT-206B-FMS-18, Rev. 3 BHT-206B3-FM-1, Rev. 18 BHT-206B3-FMS-12, Rev. 1 BHT-206B3-FMS-10, Rev. 1 (c) An alternate method of compliance, which provides an equivalent level of safety, may be used when approvedby the Manager, Helicopter Certification Branch, Federal Aviation Administration, Fort Worth, Texas 76193-0170. Airworthiness Directive 89-10-11 (Amendment 39-6211) became effective on June 8, 1989. This amendment (39-6283, AD 89-10-11 R1) becomes effective on July 31, 1989.
2010-20-20: This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) helicopters. That AD requires repetitively inspecting the main gearbox (MGB) planet gear carrier for a crack and replacing any MGB that has a cracked planet gear carrier before further flight. This action requires the same inspections required by the existing AD, but shortens the initial inspection interval. This AD is prompted by the discovery of another crack in a MGB planet gear carrier and additional analysis that indicates that the initial inspection interval must be shortened. The actions specified by this AD are intended to detect a crack in the web of the planet gear carrier, which could lead to a MGB seizure and subsequent loss of control of the helicopter.