Results
98-16-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300, A310, and A300-600 series airplanes, that requires repetitive detailed visual inspections to detect cracks in the pylon thrust and sideload fitting of the wing, and replacement of any cracked pylon thrust and sideload fitting with a new fitting. 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 detect and correct cracks in the pylon thrust and sideload fitting of the wing, which could result in reduced structural integrity of the airplane.
84-16-01: 84-16-01 MESSERSCHMITT-BOLKOW-BLOHM: Letter issued August 7, 1984. Applies to MBB Model BO 105 series helicopters certificated in all categories that are equipped with the following tail rotor blades: 105-31743 Serial Nos.: 115, 118, 219, 224, 387, 395, 581, 608, 615, 650. 105-31744 (Modification of 105-31742) Serial Nos.: 64, 86, 124, 127, 130, 131, 143, 147, 152, 158, 179, 180, 210, 211, 216, 217, 219, 220, 240, 246, 256, 262, 265, 266, 267, 269, 295, 342, 344, 372, 383, 390, 394, 414, 425, 433, 437, 438, 442, 444, 461, 467, 489, 491, 495, 499, 504, 506, 514, 516, 517, 528, 538, 543, 552, 556, 588, 591, 596, 601, 603, 607, 846, 936, 1065, 1174, 1175, 1199, 1234, 1235, 1237, 1270, 1300. Compliance required as indicated. (A) Before further flight, perform a visual check of each tail rotor blade tip area (approximately 100MM (4 inches) from end cap inward) for cracks. (B) Repeat the check of Paragraph (A) before each subsequent flight until the affected blades are replaced. (C) Replace cracked tail rotor blades with serviceable blades before further flight. (D) The check required by Paragraph (A) of this AD is not considered to be maintenance or preventive maintenance, and may be performed by the pilot, however, the person performing this check shall make an entry in the aircraft maintenance records containing the following information: The name of the person who performed the check, the date the check was accomplished, the signature, certificate number, and kind of certificate held by the person performing the check. (E) An equivalent method of compliance with this AD may be used when approved by the Manager, Aircraft Certification Division, FAA, Southwest Region, P.O. Box 1689, Fort Worth, Texas 76101. NOTE: MBB Alert Bulletin No. 23 applies to this inspection. This airworthiness directive becomes effective upon receipt.
2000-15-18: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 737-100 and -200 series airplanes, that currently requires inspections to detect cracking of the support fittings of the Krueger flap actuator; and, if necessary, replacement of existing fittings with new steel fittings and modification of the aft attachment of the actuator. That AD also provides for an optional terminating modification that constitutes terminating action for the repetitive inspections. This amendment requires accomplishment of the previously optional terminating action. This amendment is prompted by reports of cracking due to fatigue and stress corrosion of the support fittings of the Krueger flap actuator. The actions specified by this AD are intended to prevent such cracking, which could result in fracturing of the actuator attach lugs, separation of the actuator from the support fitting, severing of the hydraulic lines, and resultant loss of hydraulic fluids. These conditions, if not corrected, could result in possible failure of one or more hydraulic systems, and consequent reduced controllability of the airplane.
2019-08-07: We are superseding Airworthiness Directive (AD) 2014-20-04, which applied to all Airbus SAS Model A318 and A319 series airplanes; Airbus SAS Model A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and Airbus SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2014-20-04 required repetitive inspections of the titanium angles between the belly fairing and the keel beam side panel, an inspection of the open holes of cracked titanium angles, and corrective action if necessary. This AD continues to require those actions, adds Model A320-216 airplanes, and requires a detailed inspection for, and replacement of, certain rivets, and corrective actions if necessary. This AD was prompted by reports of cracks at the lower riveting of the four titanium angles that connect the belly fairing to the keel beam side [[Page 23462]] panels. We are issuing this AD to address the unsafe condition on these products.
2000-15-17 R1: This document corrects a typographical error that appeared in airworthiness directive (AD) 2000-15-17 that was published in the Federal Register on August 8, 2000 (65 FR 48368). The typographical error resulted in the omission of an airplane model from paragraph (c) of the AD. This AD is applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87); Model MD-88 airplanes; and Model MD-90-30 series airplanes. This AD requires installation of a pipe support and clamps on the hydraulic lines in the aft fuselage; replacement of the hydraulic pipe assembly in the aft fuselage with a new pipe assembly; and installation of drain tube assemblies and diverter assemblies in the area of the auxiliary power unit inlet; as applicable.
52-02-02: 52-02-02 ERCO: Applies to All Model 415 Series and Models E and G Aircraft. Compliance required as indicated. As a result of several Ercoupe accidents, the following precautionary measures should be taken: 1. Before the next flight and at each 25-hour inspection: (a) Inspect the aileron balance assembly (Erco P/N 415-16009) and ailerons for cracks in support structure and skin, respectively. Repair or replace defective parts. (b) Inspect the four No. 6-32 screws which attach the balance weight support to the aileron for looseness and damage. Replace defective screws with AN 526-632 screws, taking care not to overstress during tightening. 2. Before next flight and at each 100-hour inspection, thereafter, inspect the aileron hinges and aileron control system for excessive looseness or wear in hinge pins or bearings. If, with one aileron blocked in the neutral position, the total play of the other aileron, measured at the trailing edge, exceeds 7/16-inch, allthe joints and bearing should be checked and those which are loose should be tightened or replaced. 3. If the aileron balance weights have been removed in accordance with Erco Service Bulletin No. 57, item 1 above and AD 47-20-06 do not apply. However, any previous cracks in the aileron skin or beam which occurred prior to removal of the aileron balance weights must be repaired or the parts replaced. The free play referred to in item 2 above must be reduced to 5/16-inch. 4. Before the next flight, determine that the air speed instrument is distinctly marked in accordance with the operating limitations. (Engineering and Research Corp. Service Memorandum No. 56 covers this same subject.) This supersedes AD 49-02-02; the new material is contained in item 3.
2000-15-16: This amendment adopts a new airworthiness directive (AD); applicable to certain Boeing Model 737, 757, 767, and 777 series airplanes; that requires a one-time general visual inspection to determine the vendor and manufacturing date of all oxygen masks in the passenger cabin; and corrective action, if necessary. This amendment is prompted by a report that passengers were unable to activate supplemental oxygen generators during an in-flight decompression due to stress corrosion cracking of the crimped copper alloy ferrules used to secure loops on the lanyard ends. The actions specified by this AD are intended to prevent failure of the supplemental oxygen system to deliver oxygen to the passengers and flight attendants in the event of decompression, which could result in injury to passengers and flight attendants.
2019-09-02: We are superseding Airworthiness Directive (AD) 2018-17-01 for Bell Model 212, 412, 412CF, and 412EP helicopters. AD 2018-17-01 required replacing certain oil and fuel check valves and prohibited installing these valves on any helicopter. This AD retains the requirements of AD 2018-17-01 but expands those requirements for all model helicopters. This AD was prompted by the discovery that we omitted a helicopter model from one of the required actions. We are issuing this AD to address the unsafe condition on these products.
97-15-13 R1: This amendment revises Airworthiness Directive (AD) 97-15-13, which currently requires installing lubrication fittings in the airstair door handle and latch housing mechanisms on certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes (formerly referred to as Beech Models 1900, 1900C, and 1900D airplanes). Certain Model 1900C serial number airplanes were incorrectly referenced as Model 1900D airplanes in the Applicability section of AD 97-15-13. This AD maintains the requirements of AD 97-15-13, and corrects the model and serial number reference as described above. The actions specified by this AD are intended to prevent moisture from accumulating and freezing in the airstair door handle and latch housing, which could result in the door freezing shut and passengers not being able to evacuate the airplane in an emergency situation.
2006-21-03: The FAA adopts a new airworthiness directive (AD) for certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to check the maintenance records to determine whether the brake caliper piston O-ring seals were replaced at the last annual or 100-hour inspection. If the O-rings were not replaced, this AD requires you to replace the O-ring seals with new seals or replace brake calipers. This AD also requires you to modify the main landing gear wheel fairings to add temperature indicator sticker inspection holes, trim the wheel fairings to prevent them from holding fluids, install temperature indicator stickers on the brake calipers, and insert Revision A6 (with revised preflight walk-around, a limitation on the engine speed used to taxi, and brake inspection/servicing intervals) into the Pilot's Operating Handbook (POH). This AD results from several reports of airplanes experiencing brake fires and two airplanes losing directional control. We areissuing this AD to detect, correct, and prevent overheating damage to the brake caliper piston O-ring seals, which could result in leakage of brake hydraulic fluid. Consequently, this could lead to the loss of braking with loss of airplane directional control or brake fire.
2006-20-02: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747 airplanes. That AD currently requires inspections to detect disbonding, corrosion, and cracking at the longitudinal rows of fasteners in the bonded skin panels in section 41 of the fuselage, and repair, if necessary. This new AD adds airplanes to the applicability, and requires new inspections of airplanes that may have Alodine-coated rivets installed. This AD results from a report of cracking discovered in a skin lap joint that was previously inspected using the eddy current method. We are issuing this AD to prevent rapid decompression of the airplane due to disbonding and subsequent cracking of the skin panels. \n\n\nDATES: This AD becomes effective November 2, 2006. \n\nThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of November 2, 2006. \n\nOn November 27, 1996 (61 FR 57994, November 12, 1996),the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-53A2409, dated September 26, 1996.
2019-09-03: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS332C, AS332C1, AS332L, and AS332L1 helicopters. This AD requires inspecting the jettisoning mechanism of the left-hand (LH) and right-hand (RH) cabin sliding plug doors. This AD is prompted by a report that during a scheduled inspection a cabin door failed to jettison. The actions of this AD are intended to correct an unsafe condition on these products.
95-21-09: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 series airplanes, that currently requires repetitive inspections for cracking of the No. 2 flap beams, and replacement of the flap beams, if necessary. That AD was prompted by reports of cracking of the No. 2 flap beams. This amendment provides optional modifications for extending certain inspection thresholds, and an optional terminating modification for certain inspections. This amendment also expands the applicability of the existing AD to include Model A300-600 series airplanes. The actions specified by this AD are intended to prevent asymmetry of the flaps due to cracking of the No. 2 flap beams.
85-12-02: 85-12-02 PRATT & WHITNEY AIRCRAFT: Amendment 39-5072. Applies to Pratt & Whitney Aircraft JT9D-3A, -7, -7H, -7A, -7AH, -7F, and -7J series turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent centrifugal oil filter (COF) bearing failures which may initiate main gearbox fires, accomplish the following: Remove the COF, related gears, bearings, and attaching hardware from the main gearbox of PWA JT9D- 3A, -7, -7H, -7A, -7AH, -7F, and -7J series turbofan engines per PWA SB 5486, Revision 3, dated August 29, 1983, or FAA approved equivalent, when access to the removed gearbox is afforded, but not later than December 31, 1988. Upon request, an alternative means of compliance may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FARs) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Manager, Engine Certification Office, FAA New England Region, may adjust the repetitive inspection 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 that operator. The PWA SB 5486, Revision 3, dated August 29, 1983, described in this directive is 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 the SB from the manufacturer may obtain copies upon request to Pratt & Whitney Aircraft, Publication Department, P.O. Box 611, Middletown, Connecticut 06457. This document also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, Rules Docket No. 84-ANE-27, 12 New England Executive Park, Burlington, Massachusetts 01803, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on July 17, 1985.
2019-07-05: We are superseding Airworthiness Directive (AD) 2016-19-14, which applied to certain Airbus SAS Model A318 and A319 series airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2016-19-14 required repetitive inspections for cracking of the 10VU rack fitting lugs, and repair of any cracking. Since we issued AD 2016-19-14, we have determined that the unsafe condition may exist on additional airplanes. This AD continues to require repetitive inspections for cracking of the 10VU rack fitting lugs, and repair of any cracking. This AD also adds airplanes to the applicability. We are issuing this AD to address the unsafe condition on these products.
99-09-20: This amendment adopts a new airworthiness directive (AD) that is applicable to BHTC Model 222, 222B, and 222U helicopters. This action requires initial and repetitive visual inspections and verification of the torque of the bolts on the main rotor hub. This amendment is prompted by a report of fatigue cracks around the bolt holes of the main rotor pitch horn (pitch horn) and a cracked main rotor flapping bearing assembly (flapping bearing assembly) on a BHTC Model 222 helicopter. This condition, if not corrected, could result in fretting-induced fatigue cracking of the flapping bearing assembly and around the bolt holes of the pitch horn, loss of the rotor system, and subsequent loss of control of the helicopter.
2019-08-09: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 747-8 and 747-8F series airplanes. This AD was prompted by reports of damaged vapor seals, block seals, and heat shield seals on the outboard pylons between the engine strut and aft fairing. This AD requires installing new aft fairing vapor seals, heatshield seals, heatshield seal retainers, block seals, and outboard lateral restraint access panels. We are issuing this AD to address the unsafe condition on these products.
97-10-08: 97-10-08 CONSTRUCCIONES AERONAUTICAS, S.A., CASA: Amendment 39-10020. Docket 96-NM-138-AD. Applicability: Model CN-235 series airplanes, as listed in CASA Service Bulletin SB-235-52-23, Revision 2, dated June 9, 1994, and CASA Service Bulletin SB-235-52-23M, dated March 17, 1994; certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated,the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue-related cracking in the guide hooks of the cargo door, which could result in reduced structural integrity of the cargo door and, consequently, lead to rapid decompression of the airplane, accomplish the following: (a) Replace the guide hooks of the cargo doors with new, improved guide hooks, in accordance with CASA Service Bulletin SB-235-52-23, Revision 2, dated June 9, 1994, or CASA Service Bulletin SB-235-52-23M, dated March 17, 1994; at the time specified in paragraph (a)(1) or (a)(2) of this AD, as applicable. NOTE 2: Replacements accomplished prior to the effective date of this AD in accordance with CASA Service Bulletin SB-235-52-23, dated June 16, 1993, or Revision 1, dated April 13, 1994, are considered acceptable for compliance with the requirements of paragraph (a) of this AD. (1) For airplaneslisted in CASA Service Bulletin SB-235-52-23: Replace prior to the accumulation of 17,000 total landings. (2) For airplanes listed in CASA Service Bulletin SB-235-52-23M: Replace prior to the accumulation of 15,000 total landings. (b) 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, ANM-113. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement shall be done in accordance with CASA Service Bulletin SB-235-52-23, Revision 2, dated June 9, 1994, or CASA Service Bulletin SB-235-52-23M, dated March 17, 1994. CASA Service Bulletin SB-235-52-23, Revision 2, dated June 1994, contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 April 13, 1994 2 2 June 9, 1994 3-9 Original June 16, 1993 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 Construcciones Aeronauticas, S.A., Getafe, Madrid, Spain. 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. (e) This amendmentbecomes effective on June 16, 1997.
2019-08-12: We are adopting a new airworthiness directive (AD) for certain Viking Air Limited Model CL-215-6B11 (CL-215T Variant) and CL-215-6B11 (CL-415 Variant) airplanes. This AD was prompted by a report that a supplier fabricated Teflon parts with a charge of 15 percent fiberglass content instead of the specified 5 percent fiberglass content. This AD requires repetitive detailed visual inspections of the aileron control system cables and flap interconnect system cables for damage or disconnected cables, corrective actions if necessary, and replacement of the Teflon parts in the aileron control systems, aileron/rudder interconnect, and aileron power unit beam. The replacement of these parts terminates the repetitive inspections. We are issuing this AD to address the unsafe condition on these products.
98-11-31: This amendment adopts a new airworthiness directive (AD) that applies to all British Aerospace (BAe) Jetstream Model 3101 airplanes equipped with a certain autopilot. This AD requires modifying the autopilot elevator electric system relays by installing two additional relays and associated wiring changes in the relay box located under the right hand crew seat. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent failure of the autopilot elevator electric system relays for the up and down trim interlocks, which could result in uncommanded trim servo operation and possible loss of control of the airplane.
99-03-09: This amendment adopts a new airworthiness directive (AD) that is applicable to Allison Engine Company, Inc. AE 2100A, AE 2100C, and AE 2100D3 series turboprop engines. This action requires removing from service affected turbine wheels prior to exceeding new, reduced cyclic life limits. This amendment is prompted by the results of a refined life analysis. The actions specified in this AD are intended to prevent an uncontained turbine wheel failure, which could result in damage to the aircraft.
2019-08-06: We are superseding Airworthiness Directive (AD) 2016-16-01, which applied to certain Airbus SAS Model A330-200 Freighter, -200, and -300 series airplanes. AD 2016-16-01 required an inspection of affected structural parts in the cargo and cabin compartments to determine if proper heat treatment has been done, and replacement or repair if necessary. This AD retains the requirements of AD 2016-16-01 and requires inspection of additional locations of the cabin compartment structure. This AD was prompted by a report of a manufacturing defect (i.e., improperly heat-treated materials) that affects the durability of affected parts in the cargo and cabin compartments. We are issuing this AD to address the unsafe condition on these products.
2006-20-10: We are adopting a new airworthiness directive (AD) for certain Air Tractor, Inc. (Air Tractor) Models AT-802 and AT-802A airplanes. This AD requires you to repetitively inspect the attach angles on the firewall mounted hopper rinse tank shelf for damage and/or cracks and replace damaged and/or cracked attach angles with steel attach angles. Replacing the attach angles with steel attach angles terminates the repetitive inspection requirement. Reports of an uncommanded change in the engine power setting caused by separation of the hopper rinse tank shelf from the firewall prompted this AD. We are issuing this AD to detect and correct damage and/or cracks in the attach angles on the firewall mounted hopper rinse tank shelf, which could result in failure of the attach angles. This failure could lead to shelf movement under maneuver load and shifting of the engine power cables, which could result in an uncommanded engine power setting change.
98-04-25: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company Model 2000 airplanes. This action requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2006-20-03: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A319, A320, and A321 airplanes. This AD requires an inspection to determine if the stiff part of the girt and girt bar position of the forward left-hand and right-hand passenger doors is incorrect, and repair if necessary. This AD results from cases of girt bar disengagement from the floor fitting during deployment tests of slide rafts at the forward passenger doors. We are issuing this AD to prevent disengagement of the telescopic girt bar from the airplane when the door is opened in emergency situations, which could result in the inability to open the passenger door and to use the escape slide/raft at that door during an emergency evacuation of the airplane.