Results
47-47-13: 47-47-13 REPUBLIC: (Was Mandatory Note 11 of AD-769-2.) Applies to Model RC-3 Aircraft. To be accomplished not later than next 100-hour inspection or January 15, 1948. If the Hartzell propeller hub model on your airplane is HC-12X20-3, determine the counter weight length and position on the hub in order that the hub designation can be amended as necessary in accordance with the following: (a) Plain counterweights 4.650 inches in length - the designation HC-12X20-3 is unchanged. (b) Notched counterweight 4.50 inches in length - add suffix letter "C" to designation so that it reads HC-12X20-3C. (c) Plain counterweight 4.50 inches in length - a 1/8-inch slug must be added to these counterweights and suffix letter "A" added to the hub designation so that it reads HC- 12X20-3A. Any of these hubs on which the slugs have not been added to the counterweights must be removed from service until the counterweight slugs are affixed. Revise the reverse thrust operation placard as follows: For airplanes with 6A8-215-B8F engines, Serial Numbers 23001 to 23280, inclusive, and HC12X20-2 propeller: WARNING - Reversing propeller in flight prohibited. Operate reverse lever in low pitch only. Maximum 1,750 r.p.m. in reverse pitch. For airplanes with 6A8-215-B8F engines, Serial Numbers 23001 F to 23280 F, inclusive, and 23281 and up and all -B9F engines and (1) HC-12X20-3 or 3-A propellers: WARNING - Reversing propeller in flight prohibited. Operate reverse lever in low pitch only. Maximum 2,300 r.p.m. in reverse pitch. Or (2) HC-12X20-2 or -3C propellers: WARNING - Reversing propeller in flight prohibited. Operate reverse lever in low pitch only.
2024-23-03: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-300 and -400 series airplanes. This AD was prompted by a report that flight control rigging tolerances could result in spoiler deflection not reaching the minimal level required to engage the cruise thrust split monitor (MONFD) used by the autothrottle (A/T) system. This AD requires changing certain wire bundles, installing a new housing assembly, removing the mechanical aileron force limiter (MAFL), doing an inspection or records check to determine if certain flight control computers (FCCs) are installed, and performing applicable on-condition actions. The FAA is issuing this AD to address the unsafe condition on these products.
48-27-01: 48-27-01 LOCKHEED: Applies to All Model 49 Aircraft Modified to Permit Operation at 93,000 Pounds Takeoff and 83,000 Pounds Landing Weights, and Model 49 Aircraft, Redesignated as Model 149, and Modified to Permit 100,000 Pounds Takeoff and 83,000 Pounds Landing Weights. Compliance required not later than next wing change or aircraft overhaul, and in no event later than February 1, 1949. In order to comply with the requirements of Civil Air Regulations, fuel dump stand pipes must be installed. (LAC Service Bulletin 49/SB-403 and LAC Service Instruction 49/SI-12 dated September 25, 1946, cover this same subject.) Pending the accomplishment of the above change, operations are permissible at the increased weights.
2008-23-10: We are adopting a new airworthiness directive (AD) for certain Boeing Model 747 airplanes identified above. This AD requires modifying the outboard flap track and transmission attachments. This AD results from a joint Boeing and FAA multi-model study (following in-service trailing edge flap structure and drive system events) on the hazards posed by skewing and failed flaps. This study identified the safety concerns regarding the transmission attachment design and the potential loss of an outboard trailing edge flap. We are issuing this AD to prevent certain discrepancies associated with this design (for example, a flap skew or lateral control asymmetry that can cause collateral damage to adjacent hydraulic tubing and subsequent loss of a hydraulic system), which could result in the asymmetric flight control limits being exceeded, and could adversely affect the airplane's continued safe flight and landing.
2024-23-04: The FAA is superseding Airworthiness Directive (AD) 2023-21-08 for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Model Trent 1000 engines. AD 2023-21-08 required revisions to the airworthiness limitation section (ALS) of the operator's existing approved aircraft maintenance program (AMP). This AD was prompted by the manufacturer's revision of the time limits manual (TLM) to introduce new or more restrictive tasks, limitations, and associated thresholds and intervals for life-limited parts. This AD requires revisions to the ALS of the operator's existing approved AMP, 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.
2016-04-21: We are superseding Airworthiness Directive (AD) 2008-26-07 for all The Boeing Company Model DC-8-11, DC-8-12, DC-8-21, DC-8-31, DC-8- 32, DC-8-33, DC-8-41, DC-8-42, and DC-8-43 airplanes; Model DC-8-50 series airplanes; Model DC-8F-54 and DC-8F-55 airplanes; Model DC-8-60 series airplanes; Model DC-8-60F series airplanes; Model DC-8-70 series airplanes; and Model DC-8-70F series airplanes. AD 2008-26-07 required repetitive inspections of the lower skin and stringers at certain stations, and corrective actions if necessary. This new AD continues to require the actions specified in AD 2008-26-07 and also requires an eddy current high frequency (ETHF) inspection for cracks of the fastener open holes common to the lower skins, stringers, and splice fittings at a certain station; installation of external doublers and fasteners and repetitive eddy current low frequency (ETLF) inspections around the fasteners for any crack; and corrective actions if necessary. This AD was prompted bycertain mandated programs intended to support the airplane reaching its limit of validity of the engineering data that support the established structural maintenance program. We are issuing this AD to detect and correct cracks in the lower skins, stringers, and fastener holes of the splice fittings, which could result in the loss of structural integrity of the airplane.
2008-23-16: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100 & 440) airplanes. The existing AD currently requires inspecting to identify the wing anti-ice ducts (piccolo tubes) in the wing leading edge. For airplanes with affected piccolo tubes, the existing AD requires revising the airplane flight manual (AFM) to introduce new procedures for operation in icing conditions. The existing AD provides an optional implementation of repetitive inspections for cracks of affected piccolo tubes, and corrective actions if necessary, which terminates the operational limitations. The existing AD also provides an optional installation of certain new piccolo tubes, which terminates both the AFM revision and the inspections. This AD adds airplanes to the applicability, requires revising the AFM to introduce new procedures for operation in icing conditions, and requires inspecting to determine if certain anti-icepiccolo ducts are installed, and replacing or repairing the piccolo duct if necessary. This AD also provides an optional terminating action of replacing all affected piccolo ducts. This AD results from reports of failed piccolo tubes. We are issuing this AD to prevent cracked piccolo tubes, which could result in air leakage, a possible adverse effect on the anti-ice air distribution pattern and anti-ice capability without annunciation to the flight crew, and consequent reduced controllability of the airplane. DATES: This AD becomes effective December 1, 2008. The Director of the Federal Register approved the incorporation by reference of certain publications listed in the AD as of December 1, 2008. On September 7, 2005 (70 FR 49164, August 23, 2005), the Director of the Federal Register approved the incorporation by reference of certain other publications listed in the AD. We must receive any comments on this AD by December 15, 2008.
46-44-02: 46-44-02 CESSNA: (Was Mandatory Note 2 of AD-768-4.) Applies Only to 120 and 140 Aircraft Serial Numbers 8001 to 9619, Inclusive. Compliance required prior to January 1, 1947. Reinforce attachment of the safety belt brackets to the skin of the fuselage by the addition of three AN 456AD5 rivets at the safety belt end of each bracket. Make certain that the rivets pass through both bracket and fuselage skin to insure a good connection. (Cessna Service Letter No. 10-120 and 140 covers this same subject.)
2024-23-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier, Inc., Model BD-700-1A10 and BD-700-1A11 airplanes. This AD was prompted by reports of missing or damaged inboard flap seal plate assemblies. This AD requires repetitive inspections for cracks of the attaching angles of the inboard flap seal plates and replacement. The FAA is issuing this AD to address the unsafe condition on these products.
2024-23-05: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500- 1A11 airplanes. This AD was prompted by reports that the pylon-to-wing area motive flow flexible fuel line assemblies may have been installed incorrectly. This AD requires inspecting the motive flow fuel line assemblies and performing corrective actions 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.
50-10-02: 50-10-02 NAVION: Applies to all Airplanes, Serial Numbers NAV-4-2 Through NAV-4- 1790. To be accomplished as indicated below. The above aircraft employ flexible hose, Ryan Drawing 145-42202, between the exhaust shroud and the carburetor heat valve. This hose has shown a tendency to deteriorate with age and may collapse, resulting in a considerable loss of engine power. An inspection of these hoses should be made not later than March 20, 1950, and after each 25 hours of aircraft operation until replacement is made with the hose mentioned below. All hoses found to be in poor condition should be replaced immediately by wire reinforced hose. Arrowhead Rubber Co. hose type 8AX (Ryan Drawing No. 145-42202-3) or equivalent is satisfactory. The installation of the above wire reinforced air intake hose in replacement of the original hose should be accomplished in all aircraft by September 1, 1950. (Ryan Service Letter No. 67 dated February 7, 1950, also covers this subject.)
47-20-01: 47-20-01 BELLANCA (AERONCA): Amendment 39-3712. (Was Service Note 1 of AD-759-3 and Service Note 1 of AD-761-2.) Applies to Bellanca (Aeronca) Model 7AC, 7BCM, and 11AC aircraft, equipped with metal gascolator bowls, certificated in all categories. Compliance required as indicated below. 1. If the aircraft is equipped with a metal gascolator bowl that does not have a built in quick-drain arrangement, accomplish the following each 25 hours of engine operation: (a) Slowly rock the wings of the aircraft in accordance with Champion (Aeronca) supplement to "Service Helps and Hints", Nos. 15 and 18, reissued July 1, 1964, so that water lying in the fuel tank can settle into the gascolator bowl. (b) Remove the gascolator bowl and completely clean the bowl and the strainer screen to remove accumulations of water and foreign matter. NOTE: If operating conditions are such that large quantities of water are found during these inspections, the gascolator bowl should be removed more frequently and the carburetor bowl should also be drained periodically. 2. If the aircraft is equipped with a metal gascolator bowl that does have a built in quick-drain arrangement, at each annual inspection remove the gascolator bowl and completely clean the bowl and the strainer screen to remove accumulations of water and foreign matter. NOTE: Quick-drain shall be used during each pre-flight inspection. Bellanca (Champion)(Aeronca) "Service Helps and Hints", No. 15, reissued July 1, 1964; No. 18, reissued March 15, 1962; and the supplement to these bulletins, reissued July 1, 1964, also pertain to this subject. This Amendment 39-3712 becomes effective March 18, 1980.
2008-22-21: The FAA adopts a new airworthiness directive (AD) to supersede AD 78-08-09, which applies to certain Allied Ag Cat Productions, Inc. (formerly Grumman-American) (Allied Ag Cat) Models G-164, G-164A, and G-164B airplanes. AD 78-08-09 currently requires repetitively inspecting the interior and the exterior of the main tubular spar of the rudder assembly for corrosion, taking necessary corrective action if corrosion is found, and applying corrosion protection. Since we issued AD 78-08-09, the rudder main tubular spar failed on a later production airplane. Consequently, this AD retains the actions required in AD 78-08-09 and expands the applicability to include all G-164 series airplanes. We are issuing this AD to detect and correct corrosion in the rudder main tubular spar, which could result in failure of the weld to the main spar tube. This failure could lead to loss of directional control.
49-45-02: 49-45-02 CONVAIR: Applies to All Model 240 Aircraft Equipped With Curtiss Propellers. Compliance required not later than the next engine change. The following must be accomplished to insure proper operation of the throttle reverse stop override installation: 1. Rerig the reverse lock solenoid linkage, reworking and replacing parts of the linkage as shown on Figure 1, Sheets 1 and 2, of Convair Service Bulletin No. 240-273. 2. Determine that the load on the first throttle reverse detent is 15 +3, -0 pounds. 3. Remove the armature (P/N West Coast Electric Co. No. 35-31-C-3A) in the reverse throttle lock solenoid and install a new armature (P/N West Coast Electric Co. No. 35-31- C-3AS). The new armature has the letter "S" stamped on that end of the armature that has two threaded holes. (The above items are also covered by Convair Service Bulletin No. 240-273.)
2008-13-12 R1: The FAA is revising an existing airworthiness directive (AD) that applies to certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. That AD currently requires various repetitive inspections for cracking of the upper frame to side frame splice of the fuselage, and other specified and corrective actions if necessary. That AD also provides for an optional preventive modification, which terminates the repetitive inspections. This new AD adds an optional terminating action that was inadvertently omitted from that AD. This AD results from a report that the upper frame of the fuselage was severed between stringers S-13L and S-14L at station 747, and the adjacent frame at station 767 had a 1.3-inch-long crack at the same stringer location. We are issuing this AD to detect and correct fatigue cracking of the upper frame to side frame splice of the fuselage, which could result in reduced structural integrity of the frame and adjacent lap joint. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and result in decompression of the airplane. \n\n\nDATES: Effective December 1, 2008. \n\tThe Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of December 1, 2008. \n\tThe Director of the Federal Register approved the incorporation by reference of a certain other publication listed in this AD on August 12, 2008 (73 FR 38905, July 8, 2008). \n\tWe must receive comments on this AD by January 13, 2009.
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.