Results
48-09-03: 48-09-03 LUSCOMBE: Applies to Model 8 Series Airplanes Below Serial Number 5682 Equipped With Kollsman Airspeed Instruments. Compliance required by April 1, 1948. To obtain more accurate airspeed readings remove small baffle LAC P/N 181112, which is attached to the fuselage at the airspeed static tube opening. Installation of this baffle provides inaccurate airspeed readings ranging from approximately +6 m.p.h. at stall to approximately +15 m.p.h. at minimum trim speed.
96-17-09: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Beech (Raytheon) Model Hawker 1000 and BAe 125-1000A series airplanes, that currently requires inspections to detect various discrepancies of the fuel hose assemblies on the auxiliary power unit (APU), and correction of any discrepancy found. That AD was prompted by several reports of heat damage to the fuel hose assembly on the APU. This amendment adds a requirement to replace the existing conduit of the fuel feed hose with new improved conduit, which will terminate the repetitive inspections. The actions specified by this AD are intended to prevent failure of a fuel hose due to heat damage caused by incorrect routing or bleed air leakage; such failure could result in a malfunction of the APU, a fuel fire in the fuselage rear equipment bay, and reduced structural integrity of the surrounding structure. The incorporation by reference of Raytheon Service Bulletin SB 49-44, dated January 20, 1995, listed in the regulations was approved previously by the Director of the Federal Register as of May 23, 1995 (60 FR 22501, May 8, 1995)
2004-15-04: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing airplane models, that currently requires either inspections for discrepancies of the fueling float switch wiring in the center fuel tank and follow-on actions, or deactivation of the float switch. This amendment requires replacing the float switches in the center and wing fuel tanks with new, improved parts; installing a conduit liner system in the center fuel tank; and replacing conduit assemblies in the wing fuel tanks with new parts, which terminates the existing requirements. For certain airplanes, this amendment also requires replacing certain existing sections of the electrical conduit in the center fuel tank with new conduit. This amendment also adds one additional airplane model to the applicability and removes another. The actions specified by this AD are intended to prevent contamination of the fueling float switch by moisture or fuel, and chafing of the float switch wiring against the fuel tank conduit, which could present an ignition source inside the fuel tank that could cause a fire or explosion. This action is intended to address the identified unsafe condition.
72-11-04: 72-11-04 ENSTROM: Amdt. 39-1452. Applies to Model F-28A (Serial Numbers 1 through 83) helicopters. Compliance: Required as indicated, unless already accomplished. To prevent failure of tail rotor drive taper pins with subsequent loss of directional control, accomplish the following: A) Unless Paragraph B has been accomplished, within 10 hours' time in service after the effective date of this AD visually inspect the 2 forward and 3 aft AN386 taper pins installed in the tail rotor drive shaft assembly for looseness. Prior to further flight replace all loose taper pins with AN386-2-8A taper pins acquired from either the Enstrom Factory Customer Service Department, or Enstrom Dealers in accordance with Enstrom Service Note No. 0011 dated March 29, 1972, or by any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Region. NOTE: Loose pins can be detected by: 1. Wiggling the pin with the fingers. 2. Grasping the tail rotor drive shaft with the hand and rotating the shaft back and forth while observing the movement of the pin in the mating hole. 3. Examining for loss of paint on the pin at the edge of the mating hole. 4. Examining for formation of a burr at the edge of the hole. B) Within 25 hours' time in service after the effective date of this AD, replace all AN386 taper pins installed in the tail rotor drive shaft assembly with AN386-2-8A taper pins acquired from either the Enstrom Factory Customer Service Department, or Enstrom Dealers in accordance with Enstrom Service Note No. 0011 dated March 29, 1972, or by any equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Region. This amendment becomes effective June 1, 1972.
2022-06-03: The FAA is superseding Airworthiness Directive (AD) 2022-02-02 which applied to certain Bell Textron Inc. (type certificate previously held by Bell Helicopter Textron Inc.) Model 204B, 205A, 205A-1, 205B, 210, and 212 helicopters with a certain main rotor hub strap pin (pin) installed. AD 2022-02-02 required removing certain outboard pins from service and prohibited installing them on any helicopter. This AD expands the applicability to all affected pins, regardless if they are outboard or inboard. This AD also requires inspecting the removed pin for any deformation and if it is deformed, removing the mating strap fitting (fitting) from service. This AD was prompted by the discovery that AD 2022-02-02 inadvertently limited its applicability to only outboard pins when, in fact, all pins are subject to the unsafe condition and the determination that a deformed pin may have damaged the fitting. The FAA is issuing this AD to address the unsafe condition on these products.
96-17-07: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires an inspection to detect cracking of the swivel bogie beam lugs, and repair, if necessary. For airplanes on which no cracking is found, this amendment also requires an inspection to detect corrosion of the swivel pin lug surfaces and bores, and modification of the forward bogie beams. This amendment is prompted by reports indicating that swivel pin lugs of the main landing gear (MLG) have failed due to cracks resulting from stress corrosion. The actions specified by this AD are intended to prevent such stress corrosion, which could result in failure of the swivel-type bogie beam of the MLG; this condition could result in collapse of the MLG during landing.
73-22-01: 73-22-01 CESSNA: Amendment 39-1735 as amended by Amendment 39-3215. Applies to Model 340 (S/Ns 340-0001 thru 340-0234); Model 401 (S/Ns 401-0001 thru 401-0322); Model 401A (S/Ns 401A0001 thru 401A0132); Model 401B (S/Ns 401B0001 thru 401B0300); Model 402 (S/Ns 402-0001 thru 402-0322); Model 402A (S/Ns 402A0001 thru 402A0129); Model 402B (S/Ns 402B0001 thru 402B0392); Model 411 (S/Ns 411-0001 thru 411-0250); Model 411A (S/Ns 411-0251 thru 411A0300); Model 414 (S/Ns 414-0001 thru 414-0407); Model 421 (S/Ns 421-0001 thru 421-0200); Model 421A (S/Ns 421A0001 thru 421A0158); and Model 421B (S/Ns 421B0001 thru 421B0147 and S/Ns 421B0201 thru 421B0422) airplanes. Model 421 (S/N 421-0151) airplane is excepted from the requirement for the installation of Cessna Service Kit SK421-56 so long as it complies with STC SA599CE. Compliance: Required as indicated, unless already accomplished. To prevent the collection of fuel in the wing leading edge area and to provide additional instructions on preflight inspections and ground or inflight fire procedures, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: Modify the wing leading edge by installing Cessna Service Kit SK 421-56 and install applicable checklist and Flight Manual revisions as specified in Cessna Service Letter ME73-5 (Supplement 1) dated September 7, 1973, or later FAA-approved revisions, or any other modification approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Amendment 39-1735 became effective October 18, 1973. This amendment 39-3215 becomes effective on May 29, 1978.
2004-15-06: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires various inspections of the fuselage nose structure between stations 4 and 11, and corrective actions if necessary. This action is necessary to detect and correct fatigue cracking in the primary structure of the nose of the airplane at the forward avionics bay (fuselage stations 4 to 11), which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
46-42-01: 46-42-01 GLOBE: (Was Mandatory Note 4 of AD-766-5.) Applies to Models GC-1A, GC-1B Aircraft Serial Numbers 3 to 228 Inclusive. Compliance required prior to December 1, 1946. Replace the aluminum alloy cabin heater valve assembly with one constructed completely of firewall material equivalent to Globe Valve Assembly, P/N 11-440-3623. This will provide a complete firewall of firewall material. (Globe Customer Service Maintenance Bulletin No. 4 covers this same subject.)
2022-05-13: The FAA is adopting a new airworthiness directive (AD) for certain Honda Aircraft Company LLC (Honda) Model HA-420 airplanes. This AD was prompted by a report of in-flight smoke and fire that initiated from the windshield heat power wire braid. This AD requires incorporating temporary revisions into the airplane flight manual (AFM) and the quick reference handbook (QRH) that modify procedures for windshield heat operation until the affected windshield assemblies are replaced. The FAA is issuing this AD to address the unsafe condition on these products.
47-20-09: 47-20-09 ERCO: (Was Service Note 1 of AD-718-6.) Applies to 415-C, -CD and -D Aircraft. Compliance required at each 100-hour inspection and immediately after each electrical system malfunction. Check the operation of the voltage regulator by observing the ammeter reading after starting and until the battery becomes charged. A normal operation would indicate a charging rate up to 11-13 amperes for periods of time up to 20 minutes after starting. The charging rate should reduce to 2 amperes or less within 2 hours or operation. (Ercoupe Service Department Memorandum No. 23 covers this same subject.)
2022-06-10: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of three incidents involving in-flight fan blade failures on certain Pratt & Whitney engines (''fan blades'' are also known as ''1st-stage low-pressure compressor (LPC) blades''-- these terms are used interchangeably in this AD). This AD requires installation of debris shields on the thrust reverser (T/R) inner wall at the left and right sides of the lower bifurcation, inspection of the fan cowl doors for moisture ingression, repetitive functional checks of the hydraulic pump shutoff valves to ensure they close in response to the fire handle input, and corrective actions if necessary. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-25: This amendment adopts a new airworthiness directive (AD), applicable to certain Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-120 series airplanes, that requires installing a lightning bonding jumper from the lower rotating beacon to the airframe. This action is necessary to prevent possible multiple avionics failures caused by a lightning strike, which could reduce the ability of the flightcrew to control the airplane. This action is intended to address the identified unsafe condition.
93-14-16: 93-14-16 BRITISH AEROSPACE (COMMERCIAL AIRCRAFT), LIMITED: Amendment 39-8640. Docket 93-NM-03-AD. Applicability: Model ATP airplanes having aft isolator bracket attachment bolts, part number A102-4E or A102-5E; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent structural failure of the engine support structure, accomplish the following: (a) For airplanes on which the aft isolator bracket attachment bolts have accumulated less than 5,000 total landings as of the effective date of this AD: Prior to the accumulation of 5,000 total landings on the bolts, or within 1,250 hours time-in-service after the effective date of this AD, whichever occurs later, remove the bolts and replace them with new or serviceable parts, in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, dated December 9, 1992, or Revision 1, dated May 10, 1993. Thereafter, prior to the accumulation of 5,000 total landings onany bolt, replace it with a new or serviceable bolt, in accordance with the service bulletin. (b) For airplanes on which the aft isolator bracket attachment bolts will have accumulated 5,000 or more total landings before it is replaced in accordance with paragraph (a) of this AD: Prior to the accumulation of 5,000 total landings or within 150 hours time-in-service after the effective date of this AD, whichever occurs later, perform a visual inspection of the aft isolator bracket attachment bolts to determine if each bolt is in position, and to detect failed or cracked bolts, in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, dated December 9, 1992, or Revision 1, dated May 10, 1993. (1) If any bolt is missing, failed, or cracked, prior to further flight, replace all four bolts in the assembly with new or serviceable parts, in accordance with the service bulletin. Thereafter, prior to the accumulation of 5,000 total landings on any bolt, replace it with a new or serviceable bolt, in accordance with the service bulletin. (2) If no bolt is missing, failed, or cracked, repeat the visual inspection thereafter at intervals not to exceed 150 hours time-in-service. Within 1,250 hours time-in-service after the effective date of this AD, replace each bolt with a new or serviceable part, in accordance with the service bulletin. Thereafter, prior to the accumulation of 5,000 total landings on any bolt, replace it with a new or serviceable bolt, in accordance with the service bulletin. (c) Replacement of the existing bolts on the aft isolator brackets on the engine mounting beams with improved bolts (Modification 35256A) in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-10-35256A, Revision 1, dated April 16, 1993, constitutes terminating action for replacement of the bolts every 5,000 landings, as required by paragraphs (a), (b)(1), and (b)(2) of this AD. (d) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (e) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (f) The replacement and inspection shall be done in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, dated December 9, 1992; or Jetstream Aircraft, Limited, Service Bulletin ATP-54-9, Revision 1, dated May 10, 1993. The modification shall be done in accordance with Jetstream Aircraft, Limited, Service Bulletin ATP-54-10-35256A, Revision 1, dated April 16, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 April 16, 1993 2-5 0 March 2, 1993 6 (This page is not used) 7 1 (Not Dated) This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on October 4, 1993.
2022-06-11: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200 and -300 series airplanes. This AD was prompted by reports of three incidents involving in-flight fan blade failures on certain Pratt & Whitney engines (''fan blades'' are also known as ''1st-stage low- pressure compressor (LPC) blades''--these terms are used interchangeably in this AD). This AD requires modifying the engine inlet to withstand fan blade failure event loads. The FAA is issuing this AD to address the unsafe condition on these products.
2004-14-22: The FAA is adopting a new airworthiness directive (AD) for Pratt & Whitney Canada (PWC) PW206B engines that have incorporated PWC Service Bulletin (SB) No. 28119, and PW206C, PW206E, PW207D, and PW207E turboshaft engines. This AD requires checking the automatic low-cycle- fatigue (LCF) counting data made by the engine Data Collection Unit (DCU) on installed engines, and validating proper DCU automatic LCF counting before an engine is installed. This AD results from two reports of irregular LCF counting, observed between engines on the same helicopter, during weekly recording of LCF data in the engine log books. We are issuing this AD to prevent critical rotating parts from exceeding published life limits, which could result in uncontained engine failure and possible loss of the helicopter.
47-21-15: 47-21-15 REPUBLIC: (Was Mandatory Note 5 of AD-769-2.) Applies to Model RC-3 Aircraft Serial Numbers 488 to 602, Inclusive. Compliance required as soon as possible, but not later than July 1, 1947. Inspect the radio filter mounted on left-hand rear engine baffle. Filters in steel boxes 4 inches by 2 inches should be further inspected and reworked or replaced as described below, in order to minimize the possibility of a short circuit. Those filters which are in a smaller box need not be reworked. 1. If the coil is bolted to the box and the condenser is fastened in place with a clamp, the filter is satisfactory. If the coil is bolted to the box but the condenser is glued in place, the filter may be used provided a 1 1/8-inch diameter clamp is added to fasten the condenser in place. 2. Filters in which the coil is not bolted to the box should be replaced by a new filter assembly, Republic P/N SK-17-83053-1. (Republic RC-3 Seabee Service Bulletin No. 15 dated April8, 1947, covers this same subject.)
2012-22-01: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Models 172R and 172S airplanes. This AD was prompted by reports of chafed fuel return line assemblies, which were caused by the fuel return line assembly rubbing against the right steering tube assembly during full rudder pedal actuation. This AD requires you to inspect the fuel return line assembly for chafing; replace the fuel return line assembly if chafing is found; inspect the clearance between the fuel return line assembly and both the right steering tube assembly and the airplane structure; and adjust as necessary. We are issuing this AD to correct the unsafe condition on these products.
2022-05-12: The FAA is superseding Airworthiness Directive (AD) 2020-12-08 for all Embraer S.A. Model EMB-505 airplanes. AD 2020-12-08 required inspections of the mass-balance weights of the elevators, ailerons, and rudder (flight control surfaces) and their attachment parts, and corrective actions if necessary, and revising the airworthiness limitation section (ALS) of the maintenance manual or instructions for continued airworthiness to incorporate new airworthiness limitations. This AD retains the actions required by AD 2020-12-08 and requires, for certain airplanes, cleaning and weighing certain mass-balances and installation or replacement, as applicable; and for certain other mass- balances for certain airplanes, replacement of those mass-balances. This AD was prompted by a determination that new applicable airplane serial numbers and new criteria for the replacement of affected parts are necessary. The FAA is issuing this AD to address the unsafe condition on these products.
99-08-23: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This action requires repetitive inspections to detect cracking in the web of the aft pressure bulkhead at body station 1016 at the aft fastener row attachment to the "Y" chord; and corrective actions, if necessary. This amendment is prompted by several reports of fatigue cracking found at that location on Model 737 series airplanes. The actions specified in this AD are intended to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage.
84-14-01: 84-14-01 AVCO LYCOMING: Letter issued July 20, 1984. Pursuant to the authority of the Federal Aviation Act of 1958, delegated to me by the Administrator, the following AD is issued and made applicable to Avco Lycoming LTS101-600A-2 model engines. Compliance required in the sequence indicated, unless already accomplished: 1. Perform a T4 indicator system check on those AS350D helicopters having Brion Leroux T4 indicator part number 5626-524-00-00 installed, in accordance with Aerospatiale Maintenance Manual Maintenance Work Card (MWC) 77.00.00.501 at four approximately equal increments between 680 degrees C and 820 degrees C, within the next 50 engine operating hours and thereafter at intervals not to exceed 300 engine operating hours. (NOTE: Approved calibration equipment is described in Aerospatiale Telex Number AHC/SE/BH/84T/114T, paragraph EE.) Comply with following instructions (A), (B), and (C) if the T4 indicator system error is greater than zero plus minus 5 degreesC at any of the four increments and comply additionally with paragraph 4 below prior to further flight if the T4 indicator system reads low by 15 degrees C or greater at any of the four increments. (A) Check that the thermocouple loop resistance (without indicator) is not greater than 5.7 OHMS. (B) If the thermocouple loop resistance (without indicator) is greater than 5.7 OHMS, check the harness for loose or contaminated connections. Tighten, clean, or replace the aircraft harness components, or check and replace engine thermocouple components as required to bring the resistance to 5.7 OHMS or less. (C) When the thermocouple loop resistance (without indicator) is 5.7 OHMS or less, calibrate the T4 indicator system to result in zero plus minus 5 degrees C error at a selected point within the range of 760 degrees C to 770 degrees C, by adjusting the indicator setscrew (reference MWC 77.00.00.501) or replacing the indicator if required. 2. Perform an engine condition checkin accordance with the Aerospatiale AS350D helicopter flight manual, Section II, paragraph 10, within the next 50 engine operating hours. If the condition of the engine is proved to be unsatisfactory and cannot be corrected through normal maintenance procedures, comply with paragraph 4 below prior to further flight. 3. Perform an engine vibration survey in accordance with Avco Lycoming Service Bulletin Number LTS 101A-71-00-0061, Section II, Item B, within the next 50 engine operating hours. If the revised vibration limits are exceeded, comply with paragraph 4 below prior to further flight. 4. Comply with the accomplishment instructions in Avco Lycoming Service Bulletin Number LTS 101A-71-00-0061, Section II, Items F, G, H, and I, at each 600 hour periodic inspection and prior to further flight as directed by the preceding paragraphs. Aircraft may be ferried in accordance with the provisions of Federal Aviation Regulations (FAR) 21.197 and 21.199 to a base where the AD can be accomplished. Upon request of an operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, FAA, New England Region. This airworthiness directive becomes effective upon receipt.
2004-14-19: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 767 series airplanes, that requires repetitive detailed inspections of the aft pressure bulkhead for indications of oil cans and previous oil can repairs, and corrective actions, if necessary. An oil can is an area on a pressure dome web that moves when pushed from the forward side. This action is necessary to detect and correct the propagation of fatigue cracks in the vicinity of oil cans on the web of the aft pressure bulkhead, which could result in rapid decompression of the passenger cabin, possible damage or interference with the airplane control systems that pass through the bulkhead, and consequent loss of control of the airplane. This action is intended to address the identified unsafe condition.
49-13-02: 49-13-02 BELLANCA: Applies to Models 14-13, 14-13-2 and 14-13-3 Aircraft As Indicated by Serial Numbers Below. Compliance required by July 1, 1949. 1. (Applies to Serial Numbers 1060 through 1567, and 1570 through 1573.) In order to strengthen the fitting on the rear wing spar to which the landing gear drag strut attaches, Bellanca P/N 7560, a 0.065 x 1 1/4 x 1 3/8 4130 steel plate should be welded in place at the forward intersection of the two channel sections. (Bellanca Service Bulletin No. 18 covers this same subject.) 2. (Applies to all Serial Numbers prior to 1589.) In order to prevent overstressing the landing gear drag strut, a suitable stop should be provided at the lower end of the landing gear retracting screw. The stop should be so installed and adjusted as to limit the drag strut travel to that necessary to fully extend the gear. (Bellanca Service Bulletin No. 24 covers this same subject.)
2022-05-03: 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 a report that some tie-rod assemblies may have been overtightened during the installation of interior monuments (such as galleys, lavatories, and forward stowage or wardrobes). This AD requires adjusting the tie-rod assemblies, as specified in a Transport Canada Civil Aviation (TCCA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
47-21-09: 47-21-09 NAVION: (Was Mandatory Note 8 of AD-782-3.) Applies to All Serials Up to and Including Number NAV-4-947. Compliance required prior to September 1, 1947. Due to malfunctioning of the hydraulic system which has resulted in the failure of components of that system, including actuating cylinders, the following modifications must be accomplished: (a) If an engine-driven hydraulic pump is installed in the airplane, rework the hydraulic power system to install the manually controlled relief valve, North American P/N 145- 58027, and replace the existing placard "Hyd. System Pull Off" with new placard "Hyd. Power On". (North American Field Service Bulletin No. 26 covers this same subject.) (b) Install the swivel head type nose gear actuating cylinder, North American P/N 145-58014. (North American Field Service Bulletin No. 19 covers this same subject.) (c) Visually inspect all flap and landing gear actuating cylinders for evidence of cracks or other damage. Any cylinders found to be damaged should be replaced.