Results
47-34-02: 47-34-02 BEECH: (Was Mandatory Note 3 of AD-770-1 and Mandatory Note 4 of AD- 765-1.) Applies to D18S, D18C and D18C-T Airplanes Which Do Not Have Drain Provisions at Bulkhead No. 15. Compliance required prior to December 1, 1947. To provide additional drainage, to prevent freezing of trapped moisture in the tail cone which could jam the elevator control system, a 3/4-inch diameter hole should be drilled near the front of the tail cone outer section on the centerline of the lower surface. A suitable marine grommet should be installed to provide for negative pressures. Also a 1/2-inch diameter hole should be drilled on each side of the jack pad through the lower part of bulkhead No. 15. (Beech Service Bulletin D18-46 covers this same subject.)
2021-18-15: The FAA is adopting a new airworthiness directive (AD) for certain PZL Swidnik S.A. Model PZL W-3A helicopters. This AD was prompted by a report that displaced teeth were detected on the moveable assemblies of a main rotor (MR) blade droop stop. This AD requires removing from service the moveable assemblies from each affected MR blade droop stop and prohibits installation of an affected MR blade droop stop and moveable assemblies of affected MR blade droop stops. The FAA is issuing this AD to address the unsafe condition on these products.
2012-13-10: We are adopting a new airworthiness directive (AD) for the PZL Swidnik S.A. (PZL) Model PZL W-3A helicopter with a certain generator air outlet collector (collector) installed. This AD requires modifying the generator air outlet collector attachments (collector attachments). This AD is prompted by an incident where cyclic control stick movement was restricted due to rotation of a loose collector, resulting in locking of the longitudinal control system hydraulic actuator fork end. These actions are intended to prevent rotation of the collector, which could lead to restricted cyclic control stick movement, and subsequent loss of control of the helicopter.
99-06-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes. This AD requires repetitively inspecting the wing spar center web cutout on both wings for cracks between Wing Station (WS) 8 and WS 17.5, and immediately repairing any area found cracked. This repair will eliminate the need for the repetitive inspections on that particular wing spar. This AD is the result of reports of cracks in the wing spar center web cutout caused by fatigue due to airplane maneuvering and wind gusts. The actions specified by this AD are intended to detect and correct fatigue cracking of the wing spar center web cutout area, which could result in structural failure of the wing spar to the point of failure with consequent loss of control of the airplane.
2003-08-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This action requires a detailed inspection to detect cracks of the vane brackets of the inboard flap actuator beam, and follow-on repetitive detailed inspections or corrective actions, as applicable. This action also provides for two optional terminating actions for the detailed inspection(s). This action is necessary to detect and correct gaps between the flap vane bracket and the adjacent lower skin and between the flap vane bracket and vane actuator beam of the wing flap systems, and premature cracking of the flap vane brackets, which could result in failure of the flap vane bracket(s) when the flaps are extended and the flap vane is aerodynamically loaded. Loss or warping of the flap vane in flight could decrease the lift on one side of the airplane, which could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
67-32-01: 67-32-01 BRITISH AIRCRAFT CORP: Amendment 39-573. Applies to BAC 1-11 Airplanes Model/Type 212AR, 401AK, 410AQ, which have a center fuel tank fitted with Thompson Ramo fuel pumps P/N 248800/4, P/N 248800/5 or pumps manufactured under license by Plessey which include additional part number 570/1/21221/004. Amendment 39-522 (32 F.R. 17515), AD 67-32-1, is amended. Compliance required as indicated. To prevent fuel pump movement and consequent fuel leakage, accomplish the following: (a) Within the next 200 hours' time in service after the effective date of this AD, unless already accomplished, inspect the center tank fuel pump installation in accordance with BAC 1-11 Alert Service Bulletin 28-A-PM 2701, Issue 2, or later ARB-approved issue, or FAA- approved equivalent. (b) If leaks are found when conducting the inspection required by paragraph (a), before further flight stop the leaks by repositioning the fuel booster pump and, if necessary, replacing the seals between the pump and canister. (c) Within the next 1,000 hours' time in service after the effective date of this AD, modify the center tank fuel booster pumps in accordance with British Aircraft Corporation Service Bulletin No. 28-PM 2701 or later ARB-approved issue, or an equivalent approved by the Chief, Aircraft Certification Staff, European Region. This amendment becomes effective May 2, 1968.
2012-13-12: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model G-IV, GIV-X, GV, and GV-SP airplanes. This AD requires measuring to determine paint thickness on the flight control surfaces and corrective actions if necessary, and revising the Airplane Flight Manual (AFM). This AD was prompted by reports of failure to inspect or document the paint thickness on flight controls (ailerons, rudder, elevator), potentially having a negative impact on the flutter characteristics of the airplane. We are issuing this AD to detect and correct paint thickness on flight controls, which could result in loss of control of the airplane due to flutter.
99-06-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400, -400D, and -400F series airplanes, that requires modification of the P212 and P213 panels of the cabin pressure control system. For certain airplanes, this amendment also requires modification of the P5, P6, and P7 panels, and the W4701, W4703, and W4908 wire bundles, as applicable. This amendment is prompted by a report of in-flight loss of cabin pressurization control due to a single failure of the auxiliary power unit (APU) battery. The actions specified by this AD are intended to prevent loss of control of the cabin pressurization system, which could result in rapid depressurization of the airplane. Such rapid depressurization could result in deleterious physiological effects on the passengers and crew; and airplane diversions, which represent an increased risk to the airplane, passengers, and crew.
2012-13-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by a report indicating that a fire originated near the first officer's area, which caused extensive damage to the flight deck. This AD requires replacing the low-pressure oxygen hoses with non-conductive low-pressure oxygen hoses in the flight compartment. We are issuing this AD to prevent electrical current from passing through the low-pressure oxygen hose internal anti-collapse spring, which can cause the low-pressure oxygen hose to melt or burn, and a consequent oxygen-fed fire in the flight compartment.
55-15-02: 55-15-02 CONVAIR: Applies to All 240 and 340 Series Aircraft Equipped with Hamilton Standard Propellers. Compliance required by first scheduled engine change after November 1, 1955, but not later than November 1, 1956. To increase the fire resistance integrity of the propeller feathering system against damage by a powerplant fire, all flexible hose components of propeller feathering lines forward of the firewall in zone 2 must be replaced with lines and fittings which will meet current fire resistance requirements. Convair Service AirGram No. 123 dated October 8, 1954, covers this subject. The following hose assemblies may also be considered acceptable for this application: (a) Aeroquip 680-10S hose assemblies with Aeroquip 304 protective sleeves over end fittings (Aeroquip assembly P/N 304000). (b) Resistoflex-SSFR-3800-10 hose assemblies. (c) Aeroquip 309009 hose assemblies.