Results
47-51-08: 47-51-08 REPUBLIC: Applies to All Model RC-3 Airplanes with Steerable Tailwheels. Compliance required not later than the next 25-hour inspection. To preclude the possibility of the steerable tailwheel control cable fouling on the tailwheel quadrant arms, install horns 3 9/16 inches long, fabricated from 0.091 aluminum plate, pointing rearward to arms of quadrant assembly No. 17F42093-1. Drill out stop rivet and attach using AN 441-4-5 rivets. Then attach cable clips over horn and arm with AN 24-11 bolts. (Republic Service Bulletin No. 17, Supplement No. 2, dated October 16, 1947, also covers this same subject.)
2013-01-02: We are superseding an existing airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP series airplanes; and certain Model 757-200, -200PF, and -300 series airplanes. That AD currently requires replacing the control switches of the forward, aft, and nose cargo doors of Model 747 airplanes; and requires replacing the control switches of cargo doors 1 and 2 of Model 757 series airplanes. This new AD adds airplanes to the applicability and revises the initial compliance times for those airplanes. This AD was prompted by reports of problems associated with the uncommanded operation of cargo doors. We are issuing this AD to prevent injuries to persons and damage to the airplane and equipment.
2012-24-09: We are adopting a new airworthiness directive (AD) for Lycoming Engines TIO-540-AK1A, and Continental Motors, Inc. TSIO-360- MB, TSIO-360-SB, and TSIO-360-RB reciprocating engines, with certain Hartzell Engine Technologies (HET) turbochargers, model TA0411, part number (P/N) 466642-0001; 466642-0002; 466642-0006; 466642-9001; 466642-9002; or 466642-9006, or with certain HET model TA0411 turbochargers overhauled or repaired since August 29, 2012. This AD requires removing the affected turbochargers from service before further flight. This AD was prompted by a report of a turbocharger turbine wheel that failed a static strength test at its manufacturing facility. We are issuing this AD to prevent turbocharger turbine wheel failure, reduction or complete loss of engine power, loss of engine oil, oil fire, and damage to the airplane.
73-12-12: 73-12-12 BRITISH AIRCRAFT CORPORATION: Amdt. 39-1661. Applies to Viscount Series 810 airplanes. Compliance is required as indicated. To prevent a possible restriction in a power plant fire extinguisher pipe accomplish the following: Within the next 500 hours' time in service after the effective date of this AD, unless already accomplished within 5 years prior to the effective date of this AD, and thereafter at intervals not to exceed 5 years from the last replacement, replace the rubber seal sleeves P/N FRS.-F-Series 1, installed in the power plant fire extinguisher system in the pipe connector assembly located at the engine fire-proof bulkhead, with seal sleeves of the same part number. (BAC Alert Preliminary Technical Leaflet No. 149, Issue 1, dated July 30, 1971, covers this same subject). This Amendment becomes effective July 6, 1973.
47-51-03: 47-51-03 CURTISS-WRIGHT Applies to Model C-46 Series Aircraft Equipped with Aileron Closure Rib Assembly, Curtiss-Wright P/N 20-030-5039. Compliance required within every 100 hours' time in service after the effective date of this amendment until rework is accomplished. The aileron closure rib assembly 20-030-5039 has failed on some aircraft by cracking at the point of attachment to gusset and adjacent to the bolts which secure the aileron hinge assembly. 1. The rib assembly should be inspected and if cracks are found the following rework should be accomplished: (a) Remove the aileron from the airplane. (b) Remove aileron hinge assembly 20-030-5042 from the aileron closure rib 20-030-5039 located at wing station 273.875. (c) Drill out the ten 671D-5AD-5 rivets and two C71D-5AD-8 rivets which secure gusset 20-030-5039-6 to the bottom of ribs 20-030-5039-504 and 20-030-5039-505. (d) Drill out the eight AN 442AD-5 rivets which secure gusset 20-030-5039- 6 to the sides of ribs 20-030-5039-504L and 20-030-5039-505. (e) Open the inspection doors nearest each side of the aileron closure rib assembly. (f) Working through these inspection doors drill out the fourteen AN 442AD4-4 rivets which secure angles 20-030-5039-3 to the sides of the ribs 20-030-5039-504 and 20-030-5039-505. It will not be necessary to remove the twenty-eight 671D-4AD-4 rivets which secure the angles 20-030-5039-3 to the wing trailing edge closure skin. (g) Working through same inspection doors drill out the eighteen AN 442AD4-4 rivets which secure the angles 20-030-5039-506 to ribs 20-030-5039-504 and 20-030- 5039-505. The ribs are now free and can be removed from the airplane. (h) Fabricate new lower ribs 20-030-5037-504 and 20-030-5039-505 using the removed ribs as templates. (i) Fabricate one left-hand and one right-hand angle "A" 7.06 inches long x 0.90-inch leg x 0.70-inch leg, bend radius 0.09, from 0.064-24SO - ALC (AN-A-13Condition A) and heat treat to 56,000 p.s.i. (Spec. AN-QQ-H-186). (j) Fabricate one left-hand and one right-hand angle "B" 9.25 inches long x .90-inch leg x 0.70-inch leg, bend radius 0.09, from 0.064-24SO-ALC (AN-A-13 Condition A) and heat treat to 56,000 p.s.i. (Spec. AN-QQ-H-186). (k) Working through the inspection doors located in the trailing edge closure skin secure the ribs 20-030-5039-504 and 20-030-5039-505 to angles 20-030-5039-506 and 20- 030-5039-3. (l) Install angle "B" with a 0.90-inch leg against ribs 20-030-5039-504 and 20-030-5039-505 in upper inside corners of assembly using six AN 442 AD4-4 rivets for each angle. Rivet the 0.70-inch flange to top gusset using four AN 442 AD6-8 rivets outboard and five LS 1127-6-8 rivets inboard of opening in gusset. Trim angle to match openings in rib and gusset and end curvature of ribs. (m) Install angles "A" with 0.90-inch leg against ribs 20-030-5039-504 and 20-030-5039-505 in lower inside corners of assembly using two AN 442 AD4-4 rivets at inboard end and four AN 442 AD5-6 rivets to pick up leg of gusset 20-030-5039-6L and 6R and 671D- 5AD rivets on bottom. Trim end of angle to curvature of rib. (n) Drill the necessary bolt holes in ribs 20-030-5039-504 and 20-030-5039- 505 for attaching hinge assembly 20-030-5042 and install same using AN 24-8A bolts, AN 960D416 washer and AN 364-428 nuts. (o) Install the aileron. (Curtiss-Wright Service Information Letter SBS:GS:wd-1482 dated January 6, 1947, and its enclosures, also cover this same subject. This letter and its enclosures may be obtained from the Curtiss-Wright Corp., Airplane Division, Columbus, Ohio, upon request.) (p) Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, FAA Southern Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase. Revised December 28, 1964.
47-32-01: 47-32-01 BELL: (Was Mandatory Note 1 of AD-1H-1.) Applies Only to Model 47B Serial Numbers 2 Through 13. Compliance required at next 100-hour inspection. Rework the stabilizer damper frame clamp with a 1/16-inch saw cut, as shown in Bell Service Bulletin No. 47C7, revised June 12, 1947, in order to permit a clamping action which will prevent the loosening of the subject part of the main rotor mast.
2012-26-14: We are adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG BR700-715A1-30, BR700-715B1-30, and BR700-715C1-30 turbofan engines. This AD requires a one-time removal from service of the high-pressure (HP) compressor stages 1 to 6 rotor disc assembly before exceeding certain thresholds. This AD was prompted by a report of silver chloride-induced stress corrosion cracking of the HP compressor stages 1 to 6 rotor disc assembly, identified during overhaul. We are issuing this AD to prevent failure of the HP compressor stages 1 to 6 rotor disc assembly, which could result in uncontained failure of the engine and damage to the airplane.
73-15-03: 73-15-03 AVIONS MARCEL DASSAULT: Amendment 39-1688. Applies to Fan Jet Falcon airplanes, Serial Numbers 1 thru 111, which have aluminum alloy air conditioning pipes, P/N's MY20-721-28-1 and MY20-721-61-1, installed. Compliance is required as indicated. To prevent leakage of very hot air into the rear compartment, accomplish the following, unless already accomplished: (a) Within the next 100 hours' time in service after the effective date of this AD, comply with subparagraphs (1) and (2), and thereafter comply with subparagraph (1) at intervals not to exceed 200 hours' time in service from the last inspection. (1) Visually inspect the studs which retain the SEMCA coupling on pipe, P/N MY20-721-28-1, for scoring or bending, and inspect the holes receiving those studs for stretching or elongation, in accordance with Dassault Service Bulletin No. 430 (21-30) dated February 16, 1972, or an FAA-approved equivalent. (2) Inspect the weld beads and adjoining areas at the junction of the pipes, P/N's MY20-721-28-1 and MY20-721-61-1, for cracks using a magnifying glass of 5 power or greater and a dye penetrant, in accordance with Dassault Service Bulletin No. 430 (21-30) dated February 16, 1972, or an FAA-approved equivalent. (b) Within the next 100 hours' time in service after the effective date of this AD or before the accumulation of 600 hours' time in service on an aluminum alloy air conditioning pipe, P/N MY 20-721-28-1 or MY20-721-61-1, whichever occurs later (1) Replace the pipes, P/N's MY20-721-28-1 and MY20-721-61-1, with pipes of the same part number and thereafter continue to replace aluminum alloy pipes before the accumulation of 600 hours' time in service thereon and comply with paragraph (d); or (2) Replace the pipes, P/N's MY 20-721-28-1 and MY20-721-61-1, with stainless steel pipes, P/N's MY20-721-28-2 and MY20-721-61-2, in accordance with Dassault Service Bulletin No. 442 (21-31) dated February 16, 1972, oran FAA-approved equivalent. (c) If scoring or bending of the studs or stretching or elongation of the holes are found during an inspection specified in paragraph (a)(1) or cracks are found during an inspection specified in paragraph (a)(2) before further flight comply with subparagraph (1) or (2) of paragraph (b). (d) For aluminum alloy pipes installed as replacement in accordance with subparagraph (1) of paragraph (b) (1) Before the accumulation of 200 hours' time in service thereon, inspect in accordance with subparagraph (1) of paragraph (a); and (2) Thereafter, inspect in accordance with subparagraph (1) of paragraph (a) at intervals not to exceed 200 hours' time in service from the last inspection. (e) Operators who have not kept records of hours' time in service on pipes, P/N's MY20-721-28-1 and MY20-721-61-1, shall substitute airplane hours' time in service in lieu thereof. (f) The inspections required by paragraphs (a) and (d) and the replacements specified in subparagraph (1) of paragraph (b) may be discontinued when the aluminum alloy air conditioning pipes, P/N's MY20-721-28-1 and MY20-721-61-1, are replaced with stainless steel pipes, P/N's MY20-721-28-2 and MY20-721-61-2, in accordance with Dassault Service Bulletin No. 442 (21-31), dated February 16, 1972, or an FAA-approved equivalent. This amendment becomes effective August 15, 1973.
99-19-06: This amendment adopts a new airworthiness directive (AD), applicable to certain Mitsubishi Model YS-11 and YS-11A series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2022-24-06: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10, BR700-710A2-20, and BR700-710C4-11 model turbofan engines. This AD was prompted by reports of cracks on certain low-pressure compressor (LPC) rotor (fan) disks. This AD requires initial and repetitive visual inspections of certain LPC rotor fan disks and, depending on the results of the inspections, replacement of any LPC rotor fan disk with cracks detected. This AD also allows modification of the engine in accordance with RRD service information as a terminating action to these inspections, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference (IBR). The FAA is issuing this AD to address the unsafe condition on these products.
94-02-08: This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model MD-11 series airplanes. This action requires an inspection to detect chafing damage to certain wiring in the main avionics rack, repair or replacement of damaged wiring, and modification of the wiring installation. This amendment is prompted by a report of a chafed wire harness found on the main avionics rack on one airplane that resulted in arcing damage to the wire harness and adjacent structure. The actions specified in this AD are intended to prevent chafing of the main avionics rack wiring, which could result in arcing and a fire in the wire bundle; this could lead to damage to aircraft systems and loss of associated aircraft functions.
2012-27-02: We are adopting a new airworthiness directive (AD) for all Turbomeca S.A. Arriel 1A1, 1A2, 1B, 1C, 1C1, 1C2, 1D, 1D1, 1E2, 1K1, 1S, and 1S1 turboshaft engines. This AD requires performing a high gas generator speed (NG) rating vibration check. This AD was prompted by several reports of uncommanded in-flight shutdown on [[Page 2199]] Arriel 1 engines. We are issuing this AD to prevent an uncommanded in- flight shutdown of the engine, which could result in an emergency landing.
2012-26-51: We are adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires revising the airplane flight manual (AFM) to advise the flight crew of emergency procedures for addressing Angle of Attack (AoA) sensor blockage. This AD also provides for optional terminating action for the AFM revision, which involves replacing AoA sensor conic plates with AoA sensor flat plates. This AD was prompted by a report that an airplane equipped with AoA sensors installed with conic plates recently experienced blockage of all sensors during climb, leading to autopilot disconnection and activation of the alpha protection (Alpha Prot) when Mach number was increased. We are issuing this AD to prevent reduced control of the airplane.
2012-26-01: We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. This AD was prompted by reports of chafing on the bottom panel of the center cabin. This AD requires a general visual inspection to determine if certain fasteners are installed, and related investigative and corrective actions. We are issuing this AD to detect and correct any chafing on the bottom panel of the center cabin, which could affect the structural integrity of the affected wing-to-fuselage connection.
2022-10-02: The FAA is superseding Airworthiness Directive (AD) 2002-03- 01, which applied to certain Honeywell International, Inc. (Honeywell) T53 model turboshaft engines. AD 2002-03-01 required initial and repetitive special vibration tests of the engine and, if necessary, replacement with a serviceable reduction gearbox assembly, or a serviceable engine before further flight. This AD was prompted by reports of tachometer drive spur gear failure, resulting in potential engine overspeed, loss of power turbine speed (N2) instrument panel indication, and hard landings. This AD requires initial and repetitive special vibration tests of the engine and, depending on the results, replacement of either the reduction gearbox assembly or the engine. The FAA is issuing this AD to address the unsafe condition on these products.
76-04-05: 76-04-05 GRUMMAN AMERICAN: Amendment 39-2520. Applies to Grumman American Model AA-5B airplanes, Serial numbers AA5B-0001 through AA5B-0215, certificated in all categories. Compliance required within the next 20 hours' time in service after the effective date of this Airworthiness Directive, unless already accomplished. To prevent failure of the carburetor mixture control wire, replace the carburetor mixture control and modify the carburetor mixture control installation in accordance with Grumman American Aviation Corporation Service Bulletin No. 150A dated January 12, 1976 or later FAA approved revision thereto. Equivalent modifications may be approved by the Chief, Engineering and Manufacturing Branch, FAA Great Lakes Region. Special flight permits may be issued under the provisions of Federal Aviation Regulation 21.197(a)(1). The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 522(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Grumman American Aviation Corporation, 318 Bishop Road, Cleveland, Ohio 44143. These documents may also be examined at the FAA Great Lakes Region, 2300 East Devon Avenue, Des Plaines, Illinois 60018 and at FAA Headquarters, 800 Independence Avenue, S. W., Washington, D. C. A historical file on this Airworthiness Directive which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington D.C., and at the Great Lakes Region. This supersedes Amendment 39-2397, 40 F. R. 49093, AD 75-22-06. This amendment becomes effective: February 25, 1976.
99-19-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Aerospatiale Model ATR-42 and ATR-72 series airplanes, that requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This amendment is prompted by reports of inflight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to ensure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2012-26-13: We are superseding an existing airworthiness directive (AD) for all Thielert Aircraft Engines GmbH models TAE 125-01, TAE 125-02- 99, and TAE 125-02-114 reciprocating engines. That AD currently requires installation of full-authority digital electronic control (FADEC) software version 2.91. This new AD requires removing all software mapping versions prior to 292, 301, or 302, applicable to the TAE engine model. This AD was prompted by reports of possible power loss on airplanes equipped with TAE 125 engines. We are issuing this AD to prevent engine power loss or in-flight shutdown, resulting in reduced control of or damage to the airplane.
2012-26-10: We are adopting a new airworthiness directive (AD) for all Eurocopter France (Eurocopter) Model SA-365N, SA-365N1, AS-365N2, AS 365 N3, EC 155B, EC155B1, SA-365C, SA-365C1, SA-365C2, and SA-366G1 helicopters. This AD requires inspecting portions of the main gearbox (MGB) for the presence of sealing compound and corrosion. This AD was prompted by reports of corrosion on the main MGB casing lower area between the two servo-control anchoring fitting attachment ribs. An investigation determined that the corrosion was associated with sealing compound on the lower part of the fitting/casing attachment. The actions in this AD are intended to detect corrosion on the MGB casing, which could lead to a crack, failure of the MGB, and subsequent loss of control of the helicopter.
71-18-01: 71-18-01 CESSNA: Amendment 39-1275. Applies to 172 series airplanes (S/N 17248735 through 17256512). To provide correct information concerning fuel tank capacities, within the next 50 hours' time in service after the effective date of this AD, unless already accomplished, perform the following: A) Remove the existing placard on the fuel selector valve and install in its place either applicable Cessna P/N 0511167-20 placard or Cessna P/N 0500246-11 placard in accordance with Cessna Service Letter SE 68-12 dated March 12, 1968, or later FAA-approved revision, or any FAA-approved equivalent placard which would show usable fuel capacity of 18 gallons left tank, 18 gallons right tank, 36 gallons both and an off position. B) Revise the existing markings at the fuel filler necks to read: "FUEL 80/87 GRADE. TOTAL CAPACITY 19.5 GALLONS". (The operator may make and install the above markings with painted markings, using a minimum of 1/8 inch high letters.) This amendment becomes effective August 31, 1971.
98-21-22 R1: This amendment revises an existing airworthiness directive (AD), applicable to Pratt & Whitney JT9D series turbofan engines, that currently requires initial and repetitive eddy current inspections (ECI) of 14th and 15th stage high pressure compressor (HPC) disks for cracks, and removal of cracked disks and replacement with serviceable parts. This amendment revises the definition of a shop visit to make compliance less restrictive, and adds references to a Nondestructive Inspection Procedure attached to applicable service bulletins. This amendment is prompted by feedback from operators saying that the shop visit definition in the current AD made AD compliance unnecessarily restrictive. The actions specified by this AD are intended to prevent 14th and 15th stage HPC disk rupture, which could result in an uncontained engine failure and damage to the airplane.
2012-26-05: We are adopting a new airworthiness directive (AD) for all Airbus Model A330-200 Freighter series airplanes, Model A330-200 series airplanes, Model A330-300 series airplanes, Model A340-200 series airplanes, and Model A340-300 series airplanes. This AD was prompted by a report of an in-flight turn back after the nose landing gear (NLG) did not retract after take-off. This AD requires repetitive overhaul of the NLG retraction actuator. We are issuing this AD to prevent failure of the retraction actuator, which could cause collapse of the NLG after touchdown and possible injury to flightcrew and passengers.
2006-11-16: The FAA is superseding an existing airworthiness directive (AD) for AlliedSignal, Inc. T5317A-1 turboshaft engines. That AD currently requires repetitive engine fuel pump pressure tests of certain fuel control regulator assemblies to determine if both fuel pumps in the fuel control regulator assemblies are producing fuel pressure. That AD also requires replacing the fuel control regulator assembly, if necessary. This AD requires initial and repetitive visual and dimensional inspections of fuel control regulator assembly main and secondary drive shaft and pump gear splines, installed in certain fuel control regulator assemblies. This AD also expands the engine applicability, and includes certain engines installed on helicopters certified under Sec. 21.25 or 21.27 of the Code of Federal Regulations (14 CFR 21.25 or 14 CFR 21.27). This AD results from several reports of loss of fuel flow from the engine fuel control regulator assembly due to failure of both main and secondary drive shaft and pump gear splines. We are issuing this AD to prevent in-flight engine failure and forced autorotation landing.
99-23-19: This amendment adopts a new airworthiness directive (AD), applicable to certain Learjet Model 31, 31A, 35, 35A, and 60 airplanes, that requires a visual inspection of the spoiler actuators to determine the serial number of the spoiler actuators; and replacement of the spoiler actuators with new actuators, if necessary. This amendment is prompted by failure of a spoiler actuator piston rod during the first production flight of a Model 60 airplane due to an incomplete heat treatment process. The actions specified by this AD are intended to prevent failure of the spoiler actuator, which could result in the spoiler panel floating and inducing an uncommanded roll of the airplane.
75-16-14: 75-16-14 BRITISH AIRCRAFT CORPORATION: Amendment 39-2289. Applies to Model BAC 1-11, 200 and 400 Series airplanes. Compliance is required within the next 500 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible static inverter failure which could result in the loss of the A.C. emergency power supply to essential flight instruments, accomplish the following: (a) For airplanes which have not had BAC Modification 4535 incorporated, either - (1) Replace the installed Rotax static inverter, P/N U6705, with a serviceable Rotax static inverter, P/N U6705/1; or (2) Modify the installed Rotax static inverter, P/N U6705, in accordance with paragraph (c). (b) For airplanes which have had BAC Modification 4535 incorporated, either - (1) Replace the installed Rotax static inverter, P/N U6724, with a serviceable Rotax static inverter, P/N U6724/1; or (2) Modify the installed Rotax static inverter, P/N U6724, in accordance with paragraph (c). (c) Rotax static inverters, P/N U6705, may be converted to Rotax static inverters, P/N U6705/1, and Rotax static inverters, P/N U6724, may be converted to Rotax static inverters, P/N U6724/1, for compliance with paragraph (a)(2) or (b)(2) by - (1) Changing the R6 and R7 resistors on Printed Circuit Board No. 1 from 220 ohms/1.5 watt to 82 ohms/0.25 watt or 0.5 watt; and (2) Satisfying the functional tests for the modified static inverters as specified in Rotax Service Bulletin No. 24-420 at Revision 1, dated August 20, 1971 (Rotax Modification No. 4743 U) or an FAA-approved equivalent. (British Aircraft Corporation, Model BAC 1-11 Service Bulletin No. 24-PM 4992, Revision 1, dated November 8, 1971, refers to this same subject). This amendment becomes effective August 28, 1975.