Results
90-02-07: 90-02-07 AEROSPATIALE: Amendment 39-6466. Docket No. 89-NM-266-AD. Applicability: Model ATR42 series airplanes, Serial Numbers 003 through 100, certificated in any category. Compliance: Required within 30 days after the effective date of this AD, unless previously accomplished; and thereafter, compliance is required immediately following any maintenance action which could result in mis-wiring and/or mis-plumbing. To detect incorrectly installed fire protection system plumbing and/or wiring, accomplish the following: A. Conduct an inspection of the right engine fire extinguishing system wiring and plumbing in accordance with the Aerospatiale All Operators Information Message DS/E 20/89, dated December 4, 1989. If any pipes or electrical connectors are improperly installed, prior to further flight, correct the installation in accordance with the Aerospatiale message. B. An alternate means of compliance or adjustment of the compliance time, which providesan acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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 information from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse Cedex 03, France. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6466, AD 90-02-07) becomes effective on January 23, 1990.
89-21-06: 89-21-06 BRITISH AEROSPACE: Amendment 39-6346. Docket No. 89-NM-87-AD. Applicability: Model BAe 125-800A series airplanes equipped with Grumman Aerospace Corporation engine exhaust duct Part No. C46P13100-3 or C46P13100-103 (not applicable to airplanes with Dee Howard thrust reversers) certificated in any category. Compliance: Required within 180 days after the effective date of this AD, unless previously accomplished. To prevent collapse of the engine exhaust duct, accomplish the following: A. Replace the left and right engine exhaust ducts in accordance with British Aerospace Service Bulletin 71-40-3213A, Revision 2, dated April 12, 1989. B. An alternate means 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. 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 British Aerospace, PLC, Service Bulletin Librarian, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6346, AD 89-21-06) becomes effective on November 8, 1989.
2012-15-09: We are adopting a new airworthiness directive (AD) certain Airbus Model A310-203, -221, and -222 airplanes. This AD was prompted by the manufacturer re-classifying slat extension eccentric bolts as principal structural elements with replacement due at or before their calculated fatigue lives. This AD replaces certain slat extension eccentric bolts with new bolts. We are issuing this AD to prevent fatigue cracking, which could result in the loss of structural integrity of the airplane.
98-06-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB 2000 series airplanes, that requires application of sealant to the auxiliary power unit (APU) firezone bulkhead. This amendment is prompted by issuance of mandatory continued airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent hazardous amounts of flame, fuel, and vapor from entering compartments outside the fire zone due to unsealed openings in the firezone bulkhead, which could result in a fire outside the APU firezone compartment.
2012-15-03: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 190 airplanes. This AD was prompted by a report of damage on the rod end of the retracting actuator rod of the main landing gear (MLG). This AD requires performing a one-time general visual inspection to determine if a certain part number is installed on the MLG retraction actuator; if necessary, performing a general visual inspection for discrepancies between the actuator rod end and shock strut lug of the MLG retraction actuator; and corrective actions if necessary. We are issuing this AD to detect and correct breakage of the MLG retracting actuator rod, which may result in MLG extension with no hydraulic damping and consequent damage to the locking mechanism and collapse of the MLG.
2012-14-12: We are adopting a new airworthiness directive (AD) for Arrow Falcon Exporters, Inc. (previously Utah State University); Firefly Aviation Helicopter Services (previously Erickson Air-Crane Co.); California Department of Forestry; Garlick Helicopters, Inc.; Global Helicopter Technology, Inc.; Hagglund Helicopters, LLC (previously Western International Aviation, Inc.); International Helicopters, Inc.; Precision Helicopters, LLC; Robinson Air Crane, Inc.; San Joaquin Helicopters (previously Hawkins and Powers Aviation, Inc.); S.M.&T. Aircraft (previously US Helicopters, Inc., UNC Helicopter, Inc., Southern Aero Corporation, and Wilco Aviation); Smith Helicopters; Southern Helicopter, Inc.; Southwest Florida Aviation International, Inc. (previously Jamie R. Hill and Southwest Florida Aviation); Tamarack Helicopters, Inc. (previously Ranger Helicopter Services, Inc.); US Helicopter, Inc. (previously UNC Helicopter, Inc.); West Coast Fabrication; and Williams Helicopter Corporation (previously Scott Paper Co.) Model HH-1K, TH-1F, TH-1L, UH-1A, UH-1B, UH-1E, UH-1F, UH-1H, UH-1L, and UH-1P Helicopters; and Southwest Florida Aviation Model UH-1B (SW204 and SW204HP) and UH-1H (SW205) Helicopters. This AD requires [[Page 44435]] inspecting each affected tail rotor blade (blade) forward tip weight retention block (tip block) and the aft tip closure (tip closure) for adhesive bond voids and removing any blade with an excessive void from service. This AD also requires modifying certain blades by installing shear pins and tip closure rivets. This AD was prompted by reports of missing tip blocks or tip closures, resulting in minor to substantial damage to blades installed on Bell Model 212 and 412 helicopters. The actions are intended to prevent loss of a tip block or tip closure, loss of a blade, and subsequent loss of control of the helicopter.
98-06-06: This amendment adopts a new airworthiness directive (AD) that is applicable to GKN Westland Helicopters Ltd. (Westland) 30 series helicopters. This action requires determining the total hours time-in-service (TIS) of the six tail rotor drive shafts (drive shafts), creating a component history card or an equivalent record for each shaft, and replacing those drive shafts that exceed a certain TIS with an airworthy drive shaft. This amendment is prompted by findings of drive shaft attachment flange cracks on similar British military model helicopters. This condition, if not corrected, could result in failure of the drive shaft coupling attachment flanges that could result in loss of power to the tail rotor and subsequent loss of control of the helicopter.
98-06-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires replacement of the return filter diaphragm assemblies on hydraulic systems 1 and 2 with modified filter units having new diaphragms. This amendment is prompted by a report of insufficient running clearance of the brake units due to overpressure in the hydraulic return system; this condition could lead to brake overheating. The actions specified by this AD are intended to prevent too high pressure in the hydraulic return system during the selection of subsystem(s), which could result in inadvertent braking and/or blown tires.
2012-14-10: We are adopting a new airworthiness directive (AD) for CHI Model 107-II and Kawasaki Model KV107-II and KV107-IIA helicopters. This AD requires, before further flight, replacing certain upper collective pitch control yoke bolts. This AD is prompted by three failures of the affected bolts. These actions are intended to prevent failure of an upper collective pitch control yoke bolt (bolt), excessive vibration, migration of the shafts, and subsequent loss of control of the helicopter.
90-25-09: 90-25-09AEROSTAR INTERNATIONAL, INC.: Amendment 39-6848. Final copy of Priority Letter 90-25-09, Docket No. 90-CE-72-AD. Applicability: Models RX-6, RX-7, RX-8, S-49A, S-50A, S-52A, S-55A, S-57A, S- 60A, S-66A and S-77A balloons (all serial numbers) equipped with Advanced Fiber Technology (AFT) suspension cables, certificated in any category. Compliance: Required as indicated after the effective date of this AD, unless already accomplished. To prevent balloon cable degradation and loss of the balloon, accomplish the following: (a) On Models S-66A and S-77A balloons, prior to further flight replace all AFT suspension cables with stainless/galvanized steel suspension cables in accordance with the instructions in Aerostar International, Inc., Service Bulletin No. 129, dated November 28, 1990. (b) On all model balloons other than Models S-66A and S-77A with less than 100 hours time-in-service (TIS) on the AFT suspension cables, prior to further flight, andthereafter before each flight, inspect all AFT suspension cables for degradation in accordance with the instructions in Aerostar International, Inc., Service Bulletin No. 129, dated November 28, 1990. (1) If signs of degradation are found, prior to further flight replace the AFT suspension cables with stainless/galvanized steel suspension cables in accordance with the instructions in Aerostar International, Inc., Service Bulletin No. 129, dated November 28, 1990. (2) If no signs of degradation are found, return the balloon to service and reinspect before each flight until the accumulation of 100 hours TIS on the AFT suspension cables at which time paragraph (c) of this AD must be accomplished. (3) The AFT suspension cables may be replaced if no signs of degradation are found as terminating action for the inspection requirements of this AD. (c) On all model balloons other than Models S-66A and S-77A with 100 hours or more TIS on the AFT suspension cables, unlessalready accomplished per paragraph (b)(1) or (b)(3) of this AD, prior to further flight replace the AFT suspension cables with stainless/galvanized steel suspension cables in accordance with the instructions in Aerostar International, Inc., Service Bulletin No. 129, dated November 28, 1990. NOTE: Operators who do not have records of hours TIS on individual AFT suspension cables may substitute balloon hours TIS in lieu thereof. (d) The inspections and cable replacements required by this AD may be performed by the owner/operator holding at least a private pilot certificate as authorized by FAR 43.7, and must be entered into the aircraft records showing compliance with this AD in accordance with FAR 43.11. (e) When the AFT suspension cables have been replaced pursuant to this AD, the inspection requirements of this AD are no longer required. (f) An alternate method of compliance or adjustment of the compliance times that provides an equivalent level of safety may beapproved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Room 232, Des Plaines, Illinois 60018. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Chicago Aircraft Certification Office. (g) Replacement cables or copies of the applicable service information may be obtained from Aerostar International, Inc., 1813 E. Avenue, P.O. Box 5057, Sioux Falls, South Dakota 57117-5057; Telephone (605) 331-3500; or the applicable service information may be examined at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6848, AD 90-25-09) becomes effective on January 14, 1991 as to all persons except those persons to whom it was made immediately effective by priority letter AD 90-25-09, issued December 4, 1990, which contained this amendment.