Results
2016-07-31: We are superseding Airworthiness Directive (AD) 2013-22-11 for certain The Boeing Company Model 747-400 and -400D series airplanes. AD 2013-22-11 required repetitive inspections to detect cracks in the floor panel attachment fastener holes of certain upper deck floor beam upper chords, repetitive inspections, corrective actions if necessary, and replacement of the upper deck floor beam upper chords. Since we issued AD 2013-22-11, we received a report that certain fastener holes in the upper deck floor beam upper chords may not have been inspected in accordance with AD 2013-22-11. This AD adds additional repetitive inspections for cracks for certain airplanes, and corrective actions if necessary. We are issuing this AD to detect and correct fatigue cracking in certain upper chords of the upper deck floor beam. Such cracks could become large and cause the floor beams to become severed and result in rapid decompression or reduced controllability of the airplane.
2016-08-06: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300- 600 series airplanes), modified by a particular supplemental type certificate (STC). This AD was prompted by a report of chafing found on the overflow sensor harness of the surge tank, and subsequent contact between the electrical wiring and fuel tank structure. This AD requires a one-time inspection for damage of the outer tank overflow sensor harness, and repair if necessary. This AD also requires modification of the sensor harness. We are issuing this AD to prevent chafing of the harness and subsequent contact between the electrical wiring and fuel tank structure, which could result in electrical arcing and a fuel tank explosion.
73-13-09: 73-13-09 ROCKWELL INTERNATIONAL: Amdt. 39-1667. Applies to Model 690 airplanes, Serial Numbers 11001 through 11063. Compliance required within the next 50 hours time in service after the effective date of this AD, unless already accomplished. To prevent failure of oil supply lines in the event of an engine fire, accomplish the following: Remove existing oil supply hose assembly and install tube assembly (P/N 610488-111), check valve (P/N 816T-6TT (.014)-12), hose assembly (P/N 610488-113), and attaching parts as listed in Rockwell International Service Bulletin 123, dated April 5, 1973, or equivalent parts and methods approved by the Chief, Engineering and Manufacturing Branch, Southwest Region, Federal Aviation Administration, Fort Worth, Texas. This amendment becomes effective June 25, 1973.
70-10-05: 70-10-05\tBOEING: Amdt. 39-989. Applies to Model 707 and 720 series airplanes listed in Boeing Service Bulletin 2108 Revision I dated 28 December 1965. \n\n\tWithin 200 hours time in service after the effective date of this AD and after each emergency extension, inspect crank arm 65-7195 and pulley bracket 69-1087 for cracks and measure cable tension in accordance with instructions contained in the 707/720 maintenance manual. Inspections may be discontinued after modification indicated below is accomplished. \n\n\tWithin 2500 hours time in service after effective date of this AD, unless already accomplished, modify all airplanes in accordance with Boeing Service Bulletins 2108 Revision I, dated 28 December 1965 and 2108A, dated 24 May 1965, or later FAA approved revisions to these service bulletins or an equivalent modification approved by the Chief, Aircraft Engineering Division, FAA, Western Region. \n\n\tThis amendment becomes effective May 16, 1970.
2024-23-06: The FAA is adopting a new airworthiness directive (AD) for certain MD Helicopters, LLC (MDHI), Model 369, 369A, 369D, 369E, 369F, 369FF, 369H, 369HE, 369HM, 369HS, 500N, and 600N helicopters. This AD was prompted by a report of a seized and damaged roller bearing in the pilot interconnecting cyclic torque tube (torque tube) assembly. This AD requires repetitively inspecting the torque tube assembly and roller bearings, and depending on the results, replacing parts, or accomplishing additional inspections. The FAA is issuing this AD to address the unsafe condition on these products.
2016-08-04: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-223F and -243F airplanes. This AD was prompted by a report of missing fasteners in certain locations of the fuselage during production. This AD would require inspecting for missing, damaged, or incorrectly installed fasteners; and corrective actions if necessary. We are issuing this AD to detect and correct cracking of the fuselage due to missing, damaged, or incorrectly installed fasteners, which could result in reduced structural integrity of the fuselage.
2016-07-28: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87) airplanes, and Model MD-88 airplanes. This AD requires repetitive eddy current high frequency (ETHF) inspections for any cracking in the left and right side center wing lower skin, and corrective actions if necessary. This AD was prompted by reports of cracking at certain stringers, associated end fittings, and skins in the center wing fuel tank where the stringers meet the end fittings. We are issuing this AD to detect and correct cracking in the center wing lower skin. Such cracking could cause structural failure of the wings.
47-50-09: 47-50-09 FAIRCHILD: Applies to 24R and 24W Series Aircraft. Inspection required each 100 hours of operation. Inspect the landing gear fittings near the lower longeron attachment and also the fuselage fittings for cracks. Cracks in the strut not exceeding 1/8 inch in length may be repaired by electric arc welding. Cracks in excess of 1/8 inch in length should be stop drilled and oxyacetylene welded, and the landing gear strut should be re-heat-treated to 180,000 pounds per square inch. (Fairchild Service Bulletin No. 41-8 dated June 23, 1941, covers this subject.)
71-26-03: 71-26-03 SIKORSKY AIRCRAFT: Amdt. 39-1363. Applies to Sikorsky S-62A and S- 55 type Helicopters certified in all categories. Compliance required as follows: To preclude the failure of the S-62A and S-55 Servo Support Bracket P/N 1440-2415. 1. Unless already accomplished within the last 95 hours in service, inspect the servo support bracket within the next 25 hours in service after the effective date of this AD, in accordance with Part I subparagraph A and B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later FAA- approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 2. Inspect the bracket within 120 hours in service after the inspection in paragraph 1 of this airworthiness directive and every 120 hours thereafter in accordance with Part I subparagraph B of Accomplishment Instructions of Sikorsky Service Bulletins 55B40-6 or 62B40-8 as applicable dated October 1, 1971 or later approved revision or an alternate method approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 3. Conduct fluorescent magnetic particle inspection in accordance with Part II Accomplishment Instructions of SIK S/B 55B40-6 or 62B40-8 as applicable at gear box overhaul or 1250 hours, whichever comes first; or an alternate method approved by Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective December 30, 1971.
2016-08-07: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce plc (RR) RB211-22B and RB211-524 turbofan engines with low- pressure turbine (LPT) support roller bearing, part number (P/N) LK30313 or P/N UL29651, installed. This AD requires removal of certain LPT support roller bearings installed in RR RB211-22B and RB211-524 engines. This AD was prompted by a report of a breach of the turbine casing and release of engine debris through a hole in the engine nacelle. We are issuing this AD to prevent failure of the LPT support roller bearing, loss of radial position following LPT blade failure, uncontained part release, damage to the engine, and damage to the airplane.
2016-07-18: We are adopting a new airworthiness directive (AD) for certain Airbus Defense and Space S.A. Model CN-235-200 and CN-235-300 airplanes. This AD was prompted by reports of false engine fire warning events, which consequently led to engine in-flight shutdowns. This AD requires modification of the location and routing of the engine fire detection system. We are issuing this AD to prevent unnecessary engine in-flight shutdown, which could result in reduced controllability of the airplane.
67-25-04: 67-25-04 FAIRCHILD: Amdt. No. 39-472, Part 39, Federal Register May 30, 1967. Applies to Type F-27 Airplanes, Serial Numbers 108 through 123, inclusive, and FH-227 Airplanes, Serial Numbers 503, 506, through 518, 520 through 535, and 538. Due to numerous elongated and double-drilled rivet holes found in the fuselage skin, accomplish the following within the next 150 hours' time in service after the effective date of this AD unless already accomplished. (a) For F-27 Airplanes, comply with the Accomplishment Instructions of Fairchild-Hiller Service Bulletin No. 53-49 (F-27), dated April 14, 1967 and FH-227 Airplanes, comply with Accomplishment Instructions of Fairchild Hiller Service Bulletin No. 53-7 (FH-227), dated April 14, 1967, or later FAA-approved revisions, or FAA-approved equivalent modification. (b) Equivalent inspections may be approved by an FAA maintenance inspector. Equivalent parts, Service Bulletin revisions, and modifications, must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (c) Upon request with substantiating data submitted through an FAA maintenance inspector, the compliance time specified in this AD may be increased by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. This amendment effective September 8, 1967.
50-31-01: 50-31-01 CESSNA: Applies to All Models 120 and 140 Aircraft, Serial Numbers 8001 to 15035, Inclusive, on Which the 0.051 Reinforcing Channel or 0.040 Reinforcing Angles Have Not Been Installed. Compliance required as soon as possible and not later than August 1, 1950, except as indicated below. Because two fin spar fatigue failures have occurred in flight, indicating inadequate inspection due to the difficulty of such inspection, the fin must be removed for inspection. Inspection can then be best accomplished by removing five rivets in the fin bottom rib skin attachment and all attaching rivets through the spar and doubler flanges to permit raising the adjacent skin. The front face of the spar and the spar reinforcing channel should then be carefully inspected for flange buckles or cracks with at least an 8-power magnifying glass in the bend radii and in the adjacent flange rivet or clearance holes in the region of the bottom rib attachment. Modify in accordance with item 1 or 2 herein: 1. If failure exists, the spar must be replaced with a spar incorporating an 0.051 24ST alclad fin spar reinforcing channel, Cessna P/N 0431129, or equivalent. 2. If no failure exists, reinforcing angles, Cessna P/N 0431145 and 1431145-1 or equivalent, must be installed. (Cessna Service Letter No. 62 dated April 10, 1950, covers this same subject.) Some of the first airplanes were manufactured using spot welded instead of riveted construction. The following applies to these aircraft and should be accomplished not later than September 1, 1950: Drill out center of spots with No. 30 drill. Carefully pry skin loose from spar and root rib using a thin lever. Inspect and accomplish 1 or 2 above replacing all drilled spot welds with 1/8- inch rivets as required. In case that sheet or underlying structure is left with a damaged hole which cannot be properly filled with a 1/8-inch rivet, replace with 5/32-inch rivet or add an additional 1/8-inch rivet on each side of damaged hole. This supersedes AD 50-17-01.
2024-22-06: The FAA is superseding Airworthiness Directive (AD) 2023-21-06 for certain Embraer S.A. (Embraer) Model EMB-505 airplanes. AD 2023-21- 06 required installing structural reinforcements on certain monuments and replacing certain floor support rivets. Since the FAA issued AD 2023-21-06, the FAA determined that certain airplanes need to be re- assigned to a different group and certain re-identified floor support part numbers need to be corrected. This AD requires installing structural reinforcements on monuments and replacing fasteners on the floor support, as specified in an Ag[ecirc]ncia Nacional de Avia[ccedil][atilde]o Civil (ANAC) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2016-07-20: We are superseding Airworthiness Directive (AD) 95-18-08 for all Airbus Model A300-600 series airplanes. AD 95-18-08 required repetitive inspections to detect cracks in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, and repair if necessary. This new AD, for certain [[Page 21256]] airplanes, reduces the compliance times for the inspections. This AD was prompted by a report that updated fatigue and damage tolerance analyses and a fleet survey found that certain inspection thresholds and intervals must be reduced to allow more timely findings of cracking. We are issuing this AD to detect and correct fatigue-related cracking in the bottom skin of the wing in the area of the cut-out for the pylon rear attachment fitting, which could result in reduced structural integrity of the wing.
58-13-03: 58-13-03 LOCKHEED: Applies to All Model 1649A Aircraft. Compliance required as indicated. Model 1649A aircraft have been found to have possible hazardous wing bending oscillation, dynamically induced by aileron oscillation, under certain combinations of boost package tolerances and autopilot modulating piston follow-up failure. In order to correct this condition, the following must be accomplished: Modify the aileron control valve by installing a new modulating piston stop to meet limits of aileron deflection rates of 7.5 degrees per second minimum and 11 degrees per second maximum. The valve is then to be reidentified as 668152-11 and to be painted yellow to denote noninterchangeability with elevator and rudder valves. Details of the necessary modifications are given in Lockheed communication FS/225805-W, dated June 13, 1958. This modification is to be accomplished as soon as maintenance schedules will permit but not later than January 1, 1959. Until the modification is accomplished, the airplane must be flown in autopilot operation at speeds not to exceed 215 KIAS. This supersedes AD 58-11-04.
75-09-17: 75-09-17 HUGHES: Amendment 39-2191. Applies to Model 369H Series Helicopters certificated in all categories, configured with "four-on-the-floor" passenger interior in accordance with Drawing 369H90035. Compliance required as indicated unless already accomplished. To provide adequate protection for the occupants of the aft facing seats, accomplish the following: (a) Within the next 25 hours' time in service after the effective date of this AD, install two conspicuous placards worded, "DO NOT OCCUPY FOR TAKEOFF AND LANDING". The placards must be located on the aft face of the forward divider, facing aft, centered on divider, above each seat cushion. (b) Placards may be removed upon installation of a modification approved by the Chief, Aircraft Engineering Division, FAA Western Region, which provides the required occupant head and back support. This amendment becomes effective May 2, 1975.
2003-13-03: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767-200 and 767-300 series airplanes, that requires modification of the installation of the aft pressure bulkhead-to-floor insulation blankets. The actions specified by this AD are intended to prevent interference with venting during a rapid decompression in the bulk cargo compartment; such interference could cause damage to the floor structure and damage to certain control cables leading to the empennage, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2024-22-01: The FAA is superseding Airworthiness Directive (AD) 2023-05- 08, which applied to certain Airbus Canada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. AD 2023-05-08 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2023-05-08 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2016-07-17: We are superseding Airworthiness Directive (AD) 97-20-07 for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). AD 97-20-07 required repetitive inspections to detect fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar, and repair or modification of this area if necessary. This new AD reduces the inspection compliance time and repetitive inspection intervals. This AD was prompted by a determination that the inspection compliance time and repetitive inspection interval must be reduced to allow timely detection of fatigue cracking in the left and right wings in the area where the top skin attaches to the center spar. We are issuing this AD to detect and correct this fatigue cracking, which could reduce the residual strength of the top skin of the wings, and consequently [[Page 21247]] affect the structural integrity of the airframe.
2024-22-05: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 787-8, 787-9, and 787-10 airplanes. This AD was prompted by a report that during manufacture of drag brace lower lock link assemblies for the main landing gear (MLG), a certain required inspection was not performed. This AD requires doing a check of maintenance records or an inspection to determine if certain drag brace lower lock link assemblies are installed, and applicable on-condition actions. This AD also prohibits the installation of affected parts. The FAA is issuing this AD to address the unsafe condition on these products.
2024-22-07: The FAA is adopting a new airworthiness directive (AD) for certain De Havilland Aircraft of Canada Limited Model DHC-8-401 and - 402 airplanes. This AD was prompted by a report of an in-flight event where isolation valve caution messages were received. This AD requires inspecting the fuse/shuttle valve serial numbers, and replacing certain fuse/shuttle valves, as specified in a Transport Canada AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
2016-07-16: We are superseding Airworthiness Directive (AD) 2013-26-08 for certain The Boeing Company Model 737-600, -700, -700C, -800, -900, and -900ER series airplanes. AD 2013-26-08 required inspecting the orientation of both sides of the coil cord connector keyways of the number 2 windows on the flight deck; re-clocking the connector keyways, if necessary; and replacing the coil cord assemblies on both number 2 windows on the flight deck. This new AD adds airplanes to the applicability. AD 2013-26-08 resulted from reports of arcing and smoke at the left number 2 window in the flight deck. This AD was prompted by a determination that additional airplanes are subject to the same identified unsafe condition. We are issuing this AD to prevent arcing, smoke, and fire in the flight deck, which could lead to injuries to or incapacitation of the flightcrew.
47-21-04: 47-21-04 NAVION: (Was Mandatory Note 3 of AD-782-3.) Applies to Serial Numbers NAV-4-2 Through 21, 24 Through 29, 32, 35, 36, 40, 42 Through 47, 57, 192, 199, 251. To be accomplished not later than August 1, 1947. The original fuel filler scupper will collect spilled gasoline since no drain line is provided. In addition, the thickness of material is insufficient to prevent damaging by the filler hose nozzle. To eliminate these conditions, a redesigned scupper with drain line is to be installed per NAA Drawing 145-89010. (NAA Field Service Bulletin No. 2 covers this same subject.)
2016-07-12: We are adopting a new airworthiness directive (AD) for certain Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by reports of cracking of the aft fixed fairing (AFF) of the pylons due to fatigue damage of the structure. This AD requires repetitive inspections for damage and cracking of the AFF of the pylons, and repair if necessary. We are issuing this AD to detect and correct damage and cracking of the AFF of the pylons, which could result in detachment of a pylon and consequent reduced structural integrity of the airplane.