Results
2020-24-08: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (Type Certificate Previously Held by Rolls-Royce plc) (RRD) RB211 Trent 768-60, 772-60, 772B-60 and 772C-60 model turbofan engines. This AD requires replacement of high-pressure turbine (HPT) blades with parts eligible for installation before exceeding specified flight cycles since new. This AD was prompted by several reports from the manufacturer that HPT blades on RB211 Trent 700 model turbofan engines have been subject to high levels of corrosion fatigue, leading to blade cracking and eventual release, resulting in an aborted take-off and in-flight shut- downs. The FAA is issuing this AD to address the unsafe condition on these products.
78-22-06: 78-22-06 GULFSTREAM AMERICAN CORPORATION (GAC): Amendment 39- 3331. Applies to GAC Model GA-7 serial numbers GA7-0002 through GA7-0036, GA7-0038 through GA7-0043, GA7-0045, GA7-0046, and GA7-0049, airplanes certificated in all categories. Compliance is required as indicated, unless already accomplished. To prevent failure of the elevator trim control master chain and loss of elevator trim control, accomplish the following within 5 flight hours of the effective date of this AD: Inspect and modify the elevator trim control system in accordance with GAC Service Bulletin ME-6 dated October 18, 1978, or later revision approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. The inspection and/or alteration required by this AD constitute maintenance and may be performed by persons authorized to perform such maintenance under FAR 43.This amendment becomes effective November 2, 1978.
2004-01-08: This amendment adopts a new airworthiness directive (AD) that applies to Pratt & Whitney (PW) JT9D-7R4 series turbofan engines. This amendment requires on JT9D-7R4 series turbofan engines with steel fan cases, replacement of the existing one-piece fan case shield with a thicker four-piece fan case shield and would add four fan case shield supports. This amendment results from two uncontained full fan blade fracture events that resulted in penetration of the steel fan case and fan case shield. We are issuing this AD to prevent uncontained fan blade failures, resulting in damage to the airplane.
95-01-04: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 747-100 series airplanes. This action requires an inspection to detect discrepancies of the lap joint in certain fuselage stations, repair of any discrepancies, and modification of a certain lap joint. This amendment is prompted by reports of holes in the lap joints and longerons of these airplanes. The actions specified in this AD are intended to prevent reduced fatigue life of the fuselage in the areas in which holes are found.
2020-24-10: The FAA is adopting a new airworthiness directive (AD) for all Aerostar Aircraft Corporation (Aerostar) Model PA-60-601P (Aerostar 601P), PA-60-602P (Aerostar 602P), and PA-60-700P (Aerostar 700P) airplanes. This AD was prompted by reports of corrosion on the elevator and aileron balance tubes. This AD requires repetitively inspecting the elevator and aileron balance tubes for corrosion and rust and replacing the tube. The FAA is issuing this AD to address the unsafe condition on these products.
76-17-03: 76-17-03 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2699. Applies to Model Serial Number AA1, AA1A 0001 and up AA1B 0001 thru 0641 AA5 0001 and up AA-5A 0001 thru 0173, 0176 thru 0196 AA-5B 0001 thru 0309, 0311 thru 0324 airplanes certificated in all categories. Compliance required within the next 25 flight hours' time in service after the effective date of this AD, unless already accomplished. To detect delaminations in bonded skins and prevent any possible further delaminations, accomplish the following: Inspect and perform rework as prescribed by the instructions of Grumman American Aviation Corporation Service Bulletin No. 155, dated July 30, 1976, or an equivalent inspection and modification approved by the Chief, Engineering and Manufacturing Branch, Great Lakes Region. This amendment becomes effective August 30, 1976.
77-24-02: 77-24-02 SHORT BROTHERS AND HARLAND, LTD: Amendment 39-3080. Applies to SC 7 Series 3 airplanes except those modified in accordance with Shorts Modification No. 1658. Compliance is required as indicated. To detect cracks and prevent possible failure of the flap mechanism support structure, accomplish the following: (a) Before the accumulation of 5,000 landings or within 10 hours time in service after the effective date of this AD, whichever occurs later, unless already accomplished, visually inspect the flap mechanism support structure using a 10 power magnifying glass, for cracking and evidence of chafing and inadequate clearances in accordance with Part A, Steps 1 through 3, of Shorts Alert Service Bulletin No. 27-A64, Revision 3, dated September 7, 1977, (service bulletin) or an FAA-approved equivalent. (1) If cracks are found during any inspections required by this AD, that are within the acceptable limits shown in Figures 1 and 2 of the service bulletin, reinspect the flap mechanism support structure prior to each day's operation in accordance with paragraph (a) of this AD. (2) If cracks are found during any inspections required by this AD that are unacceptable in accordance with the criteria defined in Figures 1 and 2 of the service bulletin, before further flight, either replace cracked parts with new parts of the same part number, after which the aircraft may continue in service for an additional 2,400 hours time in service at which time the inspection requirements of this AD must again be complied with, or comply with paragraph (b) of this AD. (3) If no cracks are found during any inspections required by this AD, reinspect the flap mechanism support structure in accordance with paragraph (a) of this AD at intervals not to exceed 50 landings. (4) If evidence of chafing or less than minimum clearances are found during any inspections required by this AD, rework the area as shown in Figure 3 of the service bulletin or an FAA-approved equivalent, in accordance with the following compliance schedule: (i) Within 10 landings of the inspection where no cracking of structural members is found. (ii) Before further flight, if any cracking is found. (b) Compliance with the provisions of this AD may be terminated upon accomplishment of the modification of the flap mechanism support structure as shown in figure 4 of the service bulletin, or an FAA- approved equivalent. (c) For the purpose of complying with this AD, where airplane landings have not been recorded, number of landings shall be established by assuming two landings for each flight hour recorded. This amendment becomes effective November 28, 1977.
94-25-12: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Corporate Jets Model BAe 125-1000A series airplanes, that requires modification of the galley feeder cables and toilet services fuse. This amendment is prompted by a report that the gauge size of the existing galley feeder cable is not compatible with the rating of the currently used toilet services fuse. The actions specified by this AD are intended to ensure that the subject cables are compatible with the toilet services fuse in order to prevent overheating of the cables, which could result in smoke and fire in the cabin.
2008-10-10 R1: The FAA is revising an existing airworthiness directive (AD), which applies to certain Model 737-600, -700, -700C, -800, and -900 series airplanes. That AD currently requires revising the Airworthiness Limitations (AWLs) section of the Instructions for Continued Airworthiness by incorporating new limitations for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires an initial inspection to phase in certain repetitive AWL inspections, and repair if necessary. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from a design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in a fuel tank explosion and consequent loss of the airplane.
2020-26-01: The FAA is superseding Airworthiness Directive (AD) 2019-03- 18, which applied to all Airbus SAS Model A318-111, -112, -121, and - 122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; and Model A320-211, -212, -214, -216, -231, -232, and - 233 airplanes. AD 2019-03-18 required repetitive general visual inspections for cracks, and replacement if necessary, of certain main landing gear (MLG) sliding tubes that were subject to improperly performed magnetic particle inspections. This AD continues to require repetitive general visual inspections of the affected MLG sliding tubes for cracks and replacement if necessary, and requires inspections, and replacement if necessary, of additional MLG sliding tubes; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by the identification of additional MLG sliding tubes that might have been subject to the same improperly performed magnetic particle inspection. The FAA is issuing this AD to address the unsafe condition on these products.
76-10-05: 76-10-05 MOONEY: Amendment 39-2607. Applies to Models M20C (Serial Numbers 20-0010, 20-1147 through 20-1172), M20E (Serial Numbers 21-0038, 21-1161 through 21-1181, and M20F (Serial Numbers 22-1179 through 22-1272) airplanes certificated in all categories. Compliance required within the next ten hours' time in service after the effective date of this airworthiness directive unless already accomplished. To prevent fuel from leaking in the cabin as a result of a cracked diaphragm in the low fuel pressure switch, accomplish the following: (a) Remove the low fuel pressure warning system in accordance with Mooney Service Bulletin Number M20-193A dated April 1, 1976, or later FAA approved revision. A copy of this Service Bulletin can be obtained from Mooney Aircraft Corporation, Box 72, Kerrville, Texas 78028. (b) Any alternate equivalent method of compliance with this airworthiness directive must be approved by the Chief, Engineering and Manufacturing Branch, Flight StandardsDivision, Southwest Region, Federal Aviation Administration. This amendment becomes effective May 19, 1976.
2003-26-09: The FAA is superseding an existing airworthiness directive (AD) for Pratt & Whitney PW4074, PW4074D, PW4077, PW4077D, PW4084, PW4084D, PW4090, PW4090D, PW4090-3, and PW4098 turbofan engines. That AD requires initial and repetitive visual and borescope inspections of the No. 3 bearing weep tube and turbine exhaust case (TEC), and removal of the high pressure turbine (HPT) assembly and replacement of any heat distressed HPT assembly hardware if oil wetting or staining is found. This ad requires the same actions. This AD results from the finding of a significant reference error in one of the borescope inspection compliance paragraphs. We are issuing this AD to prevent thermal distressed HPT assembly hardware from remaining in service, which could result in a cracked HPT stage 1 disk or HPT stage 1-2 air seal and an uncontained engine failure.
95-12-27: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-400 series airplanes, that currently requires a revision to the input wiring for the flap control unit (FCU). This amendment requires a new systems test for the wiring of the trailing edge flap, and also expands the applicability of the existing AD to include additional airplanes. This amendment is prompted by a report indicating that a wiring error was not detected by the system test required by the existing AD. The actions specified by this AD are intended to prevent the possibility of an all-flaps-up landing due to the loss of control of all flap operations.
2003-26-06: The FAA adopts a new airworthiness directive (AD) for certain Anjou Aeronautique (ANJOU) (formerly TRW Repa S.A., formerly L'AIGLON) safety belts and restraint systems that are installed in aircraft. This AD requires you to inspect safety belts and restraint systems for defects and service life limits, and, if necessary, repair safety belts and restraint systems that have not reached service life limits; and replace safety belts and restraint systems that have reached service life limits. This AD is the result of reports of inadvertent unbuckling of the ANJOU seat belts and two safety recommendations to take AD action. We are issuing this AD to detect and correct defective safety belts and restraint systems, which could result in failure of the safety belts and restraint systems. This failure could lead to lack of occupant restraint during normal or crash loads.
76-12-09: 76-12-09 ROCKWELL INTERNATIONAL: Amendment 39-2645. Applies to Model NA-265-70 airplanes, serial numbers 370-1 through 370-9, and Model NA-265-80 airplanes, serial numbers 380-1 through 380-42 and 380-44. Compliance required as indicated, unless already accomplished. To prevent possible in flight flutter due to an improper static balance of the rudder, accomplish the following: (A) Immediately upon receipt of this AD, notify the flight crewmembers by the most practicable means, of the maximum operating limit speed: 250K/0.8M. (B) Within the next 10 hours' time in service after receipt of this AD, effect the following operating limitations and install the following placards and markings in clear view of the pilots: (1) Install a placard adjacent to each airspeed indicator that reads: "MAXIMUM OPERATING LIMIT SPEED: 250/K0.8M" (2) Mark the face of each airspeed indicator with a red radial line at 250 knots. (C) Within 60 days after receiptof this AD accomplish the following: (1) Remove the rudder from the airplane and measure the rudder's static unbalance about the hinge line using a balance measuring procedure approved by the Chief, Aircraft Engineering Division, FAA Western Region, and (2) If the static unbalance measured exceeds the limits of 0 to 5 inch-lbs leading edge heavy, before further flight adjust the static balance to be within these limits by a modification approved by the Chief, Aircraft Engineering Division, FAA Western Region. NOTE: Rockwell International intends to issue Sabreliner Service Bulletin No. 17 to provide the necessary instructions on rebalance. (D) The operating limitations, placards, and markings required by paragraph (B) may be removed after accomplishment of paragraph (C). (E) The airplane may be flown in accordance with FAR 21.197 to a base where the placards and markings required by paragraph (B) can be installed or the balance inspection and rebalance procedure of paragraph (C) can be accomplished, provided the operating limitations of paragraph (B) are not exceeded. This amendment is effective June 23, 1976 for all persons except those to whom it was made effective by airmail letter dated May 21, 1976, which contained this amendment.
2009-26-14: We are superseding an existing airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: * * * As a consequence of cracks [that were originally] detected on some CN-235 aircraft, in flap fittings P/N 35-15501-0101, -0102, -0201 and -0202, attaching the structure of the outer flaps to their rear supports and, in the adjacent structure, DGAC Spain issued AD Nr. 01/97[.] * * * Since AD 1/97 Rev.1 was published, similar cracks have been detected in flaps longerons. * * * * * * * * Fatigue cracking of the rear internal support fittings and longerons of the outer flap structure could result in failure of the outer flaps, and consequent reduced controllability of the airplane. We are issuing this AD to require actions to correctthe unsafe condition on these products.
2009-26-12: The FAA is superseding an existing airworthiness directive (AD) for Lycoming Engines (formerly Textron Lycoming) models 320, 360, and 540 series, "Parallel Valve" reciprocating engines, with certain Engine Components, Inc. (ECi) cylinder assemblies, part number (P/N) AEL65102 series "Titan," installed. That AD currently requires initial and repetitive visual inspections and compression tests to detect cracks at the head-to-barrel interface, replacement of cylinder assemblies found cracked, and replacement of certain cylinder assemblies at new, reduced times-in-service. This AD requires the same actions, but for an expanded population of cylinder assemblies. This AD results from reports of 10 additional cylinder head separations since issuing AD 2008-19-05, on cylinder serial numbers not listed in that AD. We are issuing this AD to prevent loss of engine power due to cracks at the head-to-barrel interface and possible engine failure caused by separation of a cylinder head, which could result in loss of control of the aircraft.
96-12-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes, that requires installation of reinforcement plates under each hook latch fitting on the frame of each large cargo door. For some airplanes, this amendment requires inspections to detect cracking in the area around each hook latch fitting, and repair, if necessary. This amendment is prompted by the results of stress analyses and destructive tests which revealed that fatigue-related cracking may develop in the vicinity of the hook latch fittings on the frame of the large cargo doors. The actions specified by this AD are intended to prevent reduced structural integrity of the frames of the cargo door due to fatigue cracking, which may lead to the cargo door(s) opening while the airplane is in flight.
77-16-12: 77-16-12 PRATT & WHITNEY AIRCRAFT: Amendment 39-3008. Applies to Pratt and Whitney Aircraft JT8D-1, -1A, -1B, -7, -7A, -7B, -9, -9A, -11, -15, and -17 turbofan engine models containing Number 4-1/2 bearing, P/N 707007, bearing Serial Numbers 800 through 999, and Serial Numbers 100A through 214A. Compliance required as indicated. To preclude possible low turbine shaft failure, resulting from failure of the Number 4-1/2 bearing, remove from service, prior to March 31, 1978, Number 4-1/2 bearings, P/N 707007, Serial Numbers 800 through 999, and Serial Numbers 100A through 214A. Replace with an FAA approved, serviceable 4-1/2 bearing. Affected bearings shipped in engines and shipped as spares are identified by serial number in Tables I and II of Pratt and Whitney Aircraft Alert Service Bulletin Number 4639, dated August 12, 1976, or later revision approved by the Chief, Engineering and Manufacturing Branch, New England Region. Upon request of the operator, an FAA Maintenance Inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA, New England Region, may adjust the compliance date specified in this A.D. to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. The manufacturer's service bulletin identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Pratt and Whitney Aircraft, Division of United Technologies Corporation, 400 Main Street, East Hartford, Connecticut 06108. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. This amendment becomes effective August 31, 1977.
2003-26-04: This amendment adopts a new airworthiness directive (AD) for Agusta S.p.A. (Agusta) Model A109E helicopters. This action requires certain inspections of the rod-end of the main rotor head damper for freedom of movement, and depending on the torque required to move the rod-end, either further inspection for a crack or replacing the rod-end. This amendment is prompted by reports of rod-end fractures due to fatigue failure resulting in increased helicopter vibrations. This condition, if not corrected, could result in failure of the rod-end, extreme vibrations, and a subsequent forced landing or loss of control of the helicopter.
2008-04-11 R1: The FAA is revising an existing airworthiness directive (AD), which applies to all Model 707 airplanes, and Model 720 and 720B series airplanes. That AD currently requires revising the FAA-approved maintenance program by incorporating new airworthiness limitations (AWLs) for fuel tank systems to satisfy Special Federal Aviation Regulation No. 88 requirements. That AD also requires an initial inspection to phase in certain repetitive AWL inspections, and repair if necessary. This AD clarifies the intended effect of the AD on spare and on-airplane fuel tank system components. This AD results from design review of the fuel tank systems. We are issuing this AD to prevent the potential for ignition sources inside fuel tanks caused by latent failures, alterations, repairs, or maintenance actions, which, in combination with flammable fuel vapors, could result in fuel tank explosions and consequent loss of the airplane.
94-23-09: This amendment supersedes telegraphic airworthiness directive (AD) T89-02-52, which superseded Telegraphic AD T88-22-51 (AD), applicable to Rolls-Royce, plc (R-R) Spey series turbofan engines. Telegraphic AD T88-22-51 reduced cyclic life limits for seventh stage high pressure compressor (HPC) disks from 40,000 total part cycles in service (TPC) to 35,000 TPC for the R-R Spey Model 506-14 and -14D engines. Telegraphic AD T89-02-52 currently requires repetitive inspections or further reduced cyclic life limits for seventh stage HPC disks. This amendment increases the AD's effectivity to include additional R-R Spey engine models, eliminates the option for repetitive inspections, and further reduces the cyclic life limits. This amendment is prompted by further investigation into disk bore cracking that was caused by corrosion. The actions specified by this AD are intended to prevent a seventh stage HPC disk burst due to cracking attributed to corrosion, which may result in an uncontained engine failure. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of January 6, 1995.
2020-26-17: The FAA is adopting a new airworthiness directive (AD) for all ATR--GIE Avions de Transport Regional Model ATR42-500 and ATR72 airplanes. This AD was prompted by a report of damage found on a wire bundle connecting an angle-of-attack (AOA) probe and a multi-function computer (MFC), which can inhibit activation of the stick pusher without any indication to the flight crew by the stall warning system. This AD requires a repetitive operational test for discrepancies of the stall warning system and stick pusher in the flight configuration, an inspection for discrepancies in the wiring bundles between AOA probes and MFCs, and corrective action if necessary, 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.
78-03-02: 78-03-02 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 3134. Applies to Grumman American Aviation Corporation Model G-1159 airplanes, all serial numbers certificated in all categories. COMPLIANCE: Compliance is required as indicated. To prevent possible main landing gear failures, accomplish the following: (A) Inspect the main landing gear prior to the next flight after the effective date of this A.D. to determine if part number 1159SC-L202-11 or 1159SC-L202-13 side brace/actuating cylinders are installed. (B) Within the next ten landing gear operating cycles after the effective date of this A.D., replace all P/N 1159SC-L202-13 actuators with modified units identified as 1159SC-L202- 13A in accordance with Grumman American Aviation Corporation Mandatory Customer Bulletin #261 dated January 27, 1978. (C) Within the next 100 landing gear operating cycles after the effective date of this A.D., inspect all P/N 1159SC-L202-11 actuators in accordance with Grumman American Mandatory Customer Bulletin #261 dated January 27, 1978, and if found defective, replace with modified units identified as 1159SC-L202-11A or -13A. (D) Remove from the aircraft any 1159SC-L202-11A or 1159SC-L202-13A actuator upon accumulating more than 500 actuator cycles and replace with an allowable actuator having less than 500 cycles. (E) An alternate method of compliance with paragraphs (B), (C), or (D) of this A.D. may be used if approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region. This amendment becomes effective February 3, 1978.
2003-24-12R1: The FAA is revising an existing airworthiness directive (AD) for Pratt & Whitney (PW) JT9D-3A, -7, -7A, -7F, -7H, -7AH, and -7J turbofan engines, with gearbox pressure tube, part number (P/N) 697896, and No. 4 bearing front pressure manifold, P/N 670663, installed. That AD currently requires a one-time visual inspection of the gearbox pressure tube and No. 4 bearing front pressure manifold and the attaching clamp assemblies for correct positioning and for wear and damage, and replacement if necessary. This ad requires the same actions. This AD results from the need to correct errors in depicted clamping to ensure that AD compliance can be achieved, and to relax the level of maintenance required, as an optional method, when inspecting the affected tubing for dents. We are issuing this AD to prevent engine fires caused by failed gearbox pressure tubes or failed No. 4 bearing front pressure manifolds.