Results
72-21-06: 72-21-06 AVCO LYCOMING: Amendment 39-1535. Applies to IGSO-540-A series engines except S/N 2537-50 and subsequent; and IGSO-540-B series engines except S/N 2541-50 and subsequent; and IGSO-540-A and -B engines S/N 747-50, 844-50, 852-50, 947-50, 1184-50, 1240-50, 1361-50, 1402-50, 1453-50, 1544-50, 1767-50, 1773-50, 1794-50, 1799-50, 1933-50 overhauled (also known as remanufactured) by Lycoming after 26 January 1970. To prevent shifting and possible failures of the crankcase bearings perform the following: (a) Engines that have accumulated less than 500 hours in service since new or overhaul must have the lubrication system inspected for metal contaminants within the next 10 hours in service after the effective date of this AD and every 25 hours in service thereafter. Further, at the accumulation of 525 hours in service compliance with (d) or (f) is required. (b) Engines that have accumulated 500 hours or more in service since new or overhaul must have the lubrication system inspected for metal contaminants within the next 10 hours in service after the effective date of this AD, and every 25 hours in service thereafter. Further, compliance with (d) or (f) is required within 25 hours in service after the effective date of this AD. (c) Compliance with (d) or (f) is required if metal contaminants are detected during the above inspections. (d) Remove number four cylinder and examine visually the position of number three main bearing for shifting in accordance with Part II of Avco Lycoming Service Bulletin No. 327B. Should shifting be detected, comply with paragraph (f). (e) Unless already accomplished, compliance with paragraph (f) is required within 50 hours in service after the effective date of this AD on engines that have accumulated 1200 hours or more in service since new or last overhaul. (f) Repair the crankcase as described in Lycoming Service Instructions No. 1112C and install straight crankcase bearing dowels per Lycoming Service Bulletin No. 326 or equivalent repair and alteration approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Compliance with the provisions of this paragraph eliminates the inspection requirements of this AD. This amendment is effective October 17, 1972.
47-21-20: 47-21-20 REPUBLIC: (Was Mandatory Note 10 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 426 Through 484, Except 446, 447, 452, 455, 460, 468, 471, 473, 475, 480, 481 and 483. Compliance required not later than the next 25 hours of operation subsequent to July 1, 1947, and in any case not later than September 1, 1947. In order to prevent excessive loss of oil through oil pressure gage line in case of its failure, install a restrictor fitting at the engine end of that line. (Seabee Service Bulletin No. 13, dated March 17, 1947, covers this same subject.)
47-32-09: 47-32-09 BELL: (Was Mandatory Note 9 of AD-1H-1.) Applies to Models 47B and 47B3 Helicopters. Compliance required not later than next 25-hour inspection after September 15, 1947. Diagonal external brace, 47-267-036 or 42-267-037, as applicable, should be installed on the horizontal stabilizer, of all Model 47B Series helicopters. These braces will provide external support to the stabilizers. (Bell Service Bulletin 47C21 dated June 11, 1947, covers this same subject.)
2024-21-03: The FAA is superseding Airworthiness Directive (AD) 2023-24- 06, which applies to certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000 engines. AD 2023-24-06 required revising the airworthiness limitation section (ALS) of the operator's existing approved engine maintenance or inspection program, as applicable, to incorporate new or more restrictive tasks and limitations and associated thresholds and intervals for life-limited parts. This AD was prompted by the manufacturer revising the time limits manual (TLM) to introduce new or more restrictive tasks and limitations and associated thresholds and intervals for life-limited parts. This AD requires revisions to the ALS of the operator's existing approved engine maintenance or inspection program, 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.
47-33-07: 47-33-07 BEECH: (Was Mandatory Note 2 of AD-770-1 and Mandatory Note 3 of AD- 765-1.) Applies to D18S, D18C and D18C-T Airplanes With Static Alternate Source Selector Valve. Compliance required prior to October 15, 1947. The present alternate static source does not comply with the Civil Air Regulations. The static selector valve should be removed and the AN 6270-4-22 flexible hose connected to the Beech 407-184756 static pressure tube by means of an 815-4D union. (Beech Service Bulletin D18-47 covers this same subject.)
2023-15-05: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 737 airplanes equipped with CFM International, S.A. (CFM) Model LEAP-1B series turbofan engines. This AD was prompted by a report indicating that use of engine anti-ice (EAI) in dry air for more than five minutes during certain environmental and operational conditions can cause overheating of the engine inlet inner barrel beyond the material design limit, resulting in failure of the engine inlet inner barrel and severe engine inlet cowl damage. This AD requires revising the existing airplane flight manual (AFM) to limit the use of EAI in certain conditions and revising the operator's existing minimum equipment list to prohibit dispatch under a certain item. The FAA is issuing this AD to address the unsafe condition on these products.
98-08-22: This amendment adopts a new airworthiness directive (AD) that applies to certain Pilatus Aircraft Ltd. (Pilatus) Model PC-7 airplanes. This AD requires inspecting the elevator and rudder attachment brackets for cracks and/or corrosion, and repairing or replacing any cracked or corrosion-damaged parts, as applicable. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Switzerland. The actions specified by this AD are intended to prevent failure of the elevator and rudder attachment brackets because of cracks or corrosion damage, which could result in the elevator and/or rudder separating from the airplane with consequent loss of airplane control.
2016-04-24: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 757-200 series airplanes modified by particular STCs. This AD was prompted by reports of a main cargo door being blown past its full open position while on the ground during gusty wind conditions, which resulted in uncontrolled fall down to its closed position. This AD requires installing a new placard and bracket, replacing an existing placard, and replacing the main cargo door control panel. We are issuing this AD to prevent damage to the main cargo door, which could result in rapid decompression of the airplane, or injury to maintenance and ground crew during ground operations.
2016-04-06: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. This AD was prompted by a determination that a repetitive test is needed to inspect the components on airplanes equipped with a certain air distribution system configuration. This AD requires doing repetitive testing for correct operation of the equipment cooling system and low pressure environmental control system, and corrective actions if necessary. This AD also requires, for certain airplanes, installing new relays and doing wiring changes to the environmental control system. We are issuing this AD to detect and correct latent failures of the equipment cooling system and low pressure environmental control system, which, in combination with a cargo fire event, could result in smoke in the flight deck and/or main cabin, and possible loss of aircraft control.
2003-04-25: This amendment adopts a new airworthiness directive (AD), that is applicable to Dowty Aerospace Propellers, R354/4-123-F/13, R354/4- 123-F/20, R375/4-123-F/21, R389/4-123-F/25, R389/4-123-F/26, and R390/ 4-123-F/27 propellers. This amendment requires a one-time inspection of the hub joint mating surfaces for fretting. This amendment is prompted by reports of fretting on the joint mating faces of propeller hubs. The actions specified by this AD are intended to prevent failure of the hub due to loose hub through bolts.