Results
76-07-14: 76-07-14 AERONAUTICA MACCHI: Amendment 39-2578. Applies to Models AL-60 and AL-60B airplanes, certificated in all categories. Compliance is required as indicated. To detect cracks in the engine mounting plates and to prevent possible failure of the engine mount, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, unless already accomplished, and thereafter at intervals not to exceed 50 hours time in service from the last inspection until modified in accordance with paragraph (d) of this AD, comply with the following: (1) Inspect the areas around the periphery of each of the four engine mounting plates for cracks using a dye-penetrant method. (2) Inspect the surfaces inside the concavity of each of the four engine mounting plates, where the lower shock mounts and attaching bolts are inserted, for cracks, using a dye penetrant method, in accordance with Aeronautica Macchi Mandatory Service Bulletin SB-L-0003, dated October 29, 1974, or an FAA-approved equivalent. (b) If a crack is found during an inspection required by paragraph (a) of this AD, before further flight, comply with paragraph (d) of this AD. (c) If no cracks are found during any of the inspections required by paragraph (a) of this AD, within the next 100 hours time in service after the effective date of this AD, or before the accumulation of 1200 hours total airplane time in service, whichever occurs later, comply with paragraph (d) of this AD. (d) Modify each of the four engine mounting plates by adding a reinforcement plate, P/N 6070-47, and replacing the mounting plate shim, P/N 6005, with a new designed shim, P/N 6005A, in accordance with Aeronautica Macchi Mandatory Modification Bulletin, MB-L-0001, Change 1, dated March 5, 1975, or an FAA- approved equivalent. This amendment becomes effective April 26, 1976.
2024-05-05: The FAA is adopting a new airworthiness directive (AD) for all ATR-GIE Avions de Transport R[eacute]gional Model ATR42 and ATR72 airplanes. This AD was prompted by a report of incorrect marking and assembly of the two-way valves for the left- and right-hand engine fire extinguishing systems. This AD requires accomplishing a functional check of an affected part; replacing an affected part if necessary; reporting the functional check results; and prohibiting the installation of affected parts; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2005-07-20: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-600, -700, -800, and -900 series airplanes. This AD requires installing and testing an updated version of the operational program software of the flight control computers. This AD is prompted by a report of an airplane pitching up with rapidly decreasing indicated airspeed after the flightcrew set a new altitude into the autopilot. We are issuing this AD to prevent anomalous autopilot operation that produces a hazardous combination of airplane attitude and airspeed, which could result in loss of control of the airplane.
78-12-11: 78-12-11 BRITISH AEROSPACE, INC.: Amendment 39-3237. Applies to (Hawker Siddeley) Model HS-125 Series 700A Airplanes, serial numbers NA 0201 thru NA 0210 and NA 0218, certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent electrical overload and possible fire, accomplish the following in accordance with Section 2, "ACCOMPLISHMENT INSTRUCTIONS" of British Aerospace (formerly Hawker Siddeley Aviation Ltd.) Service Bulletin 24-203 (2653), dated December 14, 1977, or an FAA approved equivalent. (a) Within 10 hours time in service after the effective date of this AD, replace the existing Minyvin 20 beacon light cable and associated marker sleeves and terminal lugs with Minyvin 16 cable and associated B25Y marker sleeves and 36151 terminal lugs or with parts specified in paragraph (b) of this AD. (b) Nyvin 16 or MIL-W-5086 Series 2 cable may be used as alternate replacement cables. Also, FAA approved equivalent marker sleeves including single sleeves with indelible coding may be used in lieu of B25Y sleeves. This amendment becomes effective June 26, 1978.
97-08-07: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-80 series airplanes and Model MD-88 airplanes, that currently requires an inspection to determine the type of fluorescent light ballasts installed in the cabin sidewall; and installation of a protective cover on the ballast, replacement, or removal/disconnection of the ballast, if necessary. That action also requires, for some airplanes, removal of the dust barriers from the outboard ceiling panels, and installation of modified outboard ceiling panels. This amendment would add a requirement to replace certain ballasts on which a protective cover is installed with other ballasts, or removal/disconnection of the ballast. This amendment is prompted by additional reports of heavy smoke and fumes emitting from the ceiling panels in the forward passenger cabin due to the failure of the fluorescent light ballasts. The actions specified in this AD are intended to prevent a fire in the passenger compartment, which could result from failure of the fluorescent light ballast of the upper and lower cabin sidewall, and consequent failure of the dust barriers of the outboard ceiling panel.
2024-03-09: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A11 airplanes. This AD was prompted by a manufacturing issue with an electrical connector that may prevent the connector from self-locking. This AD requires removing the affected connector, installing a new connector, and testing the emergency power supply units (EPSUs), as specified in a Transport Canada AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
76-21-07: 76-21-07 BRITTEN-NORMAN LTD: Amendment 39-2752. Applies to Models BN-2A and BN-2A MK III airplanes, all series, certificated in all categories. Compliance is required within the next 25 hours time in service after the effective date of this AD or before 2 years since new, whichever occurs later, unless already accomplished. To detect corrosion and cracks on the forward face of the engine mounting brackets and prevent possible engine separation, accomplish the following: (a) Inspect the forward face of the engine mounting brackets, P/N NB-20-3463 (BN- 2A) and P/N NB-20-5781 (BN-2A MK III), for corrosion and cracks, in accordance with paragraphs 1 and 2 of the section entitled "Inspection" of Britten-Norman Service Bulletin BN-2/SB,91, issue 1, dated March 23, 1976, or an FAA-approved equivalent. (b) If, during the inspection required by paragraph (a) of this AD, no corrosion is found, re-assemble the engine mounting brackets in accordance with paragraphs 3 and 4of the section entitled "Inspection" of Britten-Norman Service Bulletin BN-2/SB, 91, issue 1, dated March 23, 1976, or an FAA-approved equivalent. (c) If, during the inspection required by paragraph (a) of this AD, minor surface corrosion is found and the bracket surface is free of any pitting, repair and re-assemble the engine mounting brackets in accordance with paragraph 1 of the section entitled "Rectification" of Britten-Norman Ltd. Service Bulletin BN-2/SB.91, issue 1, dated March 23, 1976, or an FAA- equivalent. (d) If, during the inspection required by paragraph (a) of this AD, severe corrosion which is evidenced by surface pitting or a crack is found, replace the engine mounting brackets with new parts of the same part number in accordance with paragraph 2 of the section entitled "Rectification" of Britten-Norman Ltd., Service Bulletin BN-2/SB.91, issue 1, dated March 23, 1976, or an FAA-approved equivalent. This amendment becomes effective November 5, 1976.
2005-07-14: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD requires an inspection of the spoiler servo control for certain part numbers, and corrective action if necessary. This AD is prompted by a report of a broken piston rod bearing of the spoiler servo control. We are issuing this AD to prevent breakage of the piston rod bearing, which could cause loss of the associated hydraulic system and spoiler extension, and could result in reduced controllability of the airplane.
97-08-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 777-200 series airplanes. This action requires repetitive visual inspections of the forward mounts of certain engines to detect damaged, missing, or failed parts, and eventual modification of those engines. Accomplishment of this modification terminates the requirement for repetitive inspections. This amendment is prompted by a report indicating that bolts that attach the yoke of the forward mount to the fan case of the engine have failed due to fatigue cracking. The actions specified in this AD are intended to prevent fatigue cracking in these bolts, which could lead to failure of these bolts and consequent separation of the engine from the wing.
2024-03-06: The FAA is superseding Airworthiness Directive (AD) 2021-20- 13, which applied to certain Bombardier, Inc., Model CL-600-2B16 (604 Variant) airplanes. AD 2021-20-13 required repetitive lubrication and repetitive detailed visual inspections (DVI) and non-destructive test (NDT) inspections of the main landing gear (MLG) shock strut lower pins, and replacement if necessary. This AD continues to require the lubrication and inspections specified in AD 2021-20-13 until the MLG shock strut assembly is modified by replacing the trailing arm bushing and installing new dynamic joint components. This AD was prompted by a new design solution for this potential failure of the shock strut lower pin. The FAA is issuing this AD to address the unsafe condition on these products.