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2021-25-12: The FAA is superseding Airworthiness Directive (AD) 2017-19- 09, which applied to certain De Havilland Aircraft of Canada Limited (Type Certificate Previously Held by Bombardier, Inc.) Model DHC-8-400 series airplanes. AD 2017-19-09 required modifying the nose landing gear (NLG) shock strut assembly. This new AD requires repetitive lubrications of the trailing arm of the NLG. This new AD also requires revising the existing maintenance or inspection program to include new and revised airworthiness limitations (life limits for certain bolts). This AD was prompted by reports of a certain bolt being found missing or having stress corrosion cracking. The FAA is issuing this AD to address the unsafe condition on these products.
93-06-07: 93-06-07 DE HAVILLAND, INC.: Amendment 39-8532. Docket 92-NM-81-AD. Applicability: Model DHC-7 series airplanes, serial numbers 003 through 113, inclusive; Model DHC-8-102 and -103 series airplanes, serial numbers 003 through 321, inclusive; and Model DHC-8-301 and -311 series airplanes, serial numbers 100 through 320, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the loss of both hydraulic systems due to depletion of hydraulic fluid, accomplish the following: (a) For Model DHC-7 series airplanes: Within 1,000 hours time-in-service after the effective date of this AD, or within 6 months after the effective date of this AD, whichever occurs first, remove the existing Quantity Limiting Valves (QLV), from the left- and right-hand inboard nacelles; and modify or replace them with new QLV, Modification 7/2610; in accordance with de Havilland Service Bulletin S.B. 7-29-20, dated March 20, 1992. (b) For Model DHC-8-102 and -103 series airplanes and Model DHC-8-301 and -311 series airplanes that have accumulated 6,700 total hours time-in-service or more as of the effective date of this AD, or if 50 months or more have passed since the airplane was manufactured as of the effective date of this AD: Within 1,000 hours time-in-service after the effective date of this AD, or within 6 months after the effective date of this AD, whichever occurs first, remove the existing QLV from the left- and right-hand inboard nacelles; and modify or replace them with new QLV, Modification 8/1803; in accordance with de Havilland Service Bulletin S.B. 8-29-21, dated March 20, 1992. (c) For Model DHC-8-102 and -103 series airplanes and Model DHC-8-301 and -311 series airplanes that have accumulated less than 6,700 total hours time-in-service as of the effective date of this AD and if less than 50 months have passed since the airplane was manufactured as of the effective date of this AD:Prior to the accumulation of 7,700 hours time-in-service since the airplane was manufactured, or within 12 months after the effective date of this AD, whichever occurs first, remove the existing QLV from the left- and right-hand inboard nacelles; and modify or replace them with new QLV, Modification 8/1803; in accordance with de Havilland Service Bulletin S.B. 8-29-21, dated March 20, 1992. (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, New York Aircraft Certification Office (ACO), FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (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 removal, modification, and replacement shall be done in accordance with de Havilland Service Bulletin S.B. 7-29-20, dated March 20, 1992 (for Model DHC-7 series airplanes); or de Havilland Service Bulletin S.B. 8-29-21, dated March 20, 1992 (for Model DHC-8-102 and -103 series airplanes and Model DHC-8-301 and -311 series airplanes); as applicable. 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 de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Engine and Propeller Directorate, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 12, 1993.
94-04-18: This amendment supersedes Airworthiness Directive (AD) 92-24-01, which currently requires inspecting the elevator balance arm assemblies of certain Beech Aircraft Corporation Models 34C and T34C-1 airplanes to ensure that sufficient welds exist to secure the balance weight tube to the attachment plate, and also requires replacing the assembly if insufficient welds are found. The Federal Aviation Administration (FAA) has determined that the existing AD should also apply to certain Beech Model T34C airplanes. This action retains the requirements of AD 92-24-01 and incorporates these Beech Model T34C airplanes. The actions specified by this AD are intended to prevent separation of an elevator balance arm assembly from the elevator because of an insufficient weld, which could result in loss of control of the airplane.
2004-12-12: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes. This action requires repetitive inspections for cracks or evidence of damage/distortion of the anti-skid drive coupling clips for the hubcaps of the main landing gear (MLG) wheels; repetitive measurement of the gap and height dimensions of the coupling clips; corrective actions, if necessary; and eventual replacement of all coupling clips with new, improved coupling clips. This action is necessary to prevent excessive gaps in the anti-skid drive coupling clips for the hubcaps of the MLG, which could result in momentary loss of the normal braking system at low speeds, and reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2012-12-01: We are superseding an existing airworthiness directive (AD) for all Airbus Model A300 B4-600, B4-600R and A300 F4-600R series airplanes, Model A300 C4-605R Variant F airplanes, and Model A310 series airplanes. That AD currently requires modifying the wiring in the right-hand electronics rack. This new AD requires replacing the cockpit multi-tank indicators (MTI), and for certain airplanes, replacing high-level, low-level, and overflow sensors and their harness connectors, and re-instating the low-level warning indication to the cockpit MTI. This AD was prompted by reports of failures of four fuel level sensor-amplifier and MTI units. This AD also adds Model A310 series airplanes to the applicability. We are issuing this AD to prevent degradation of the electrical insulation sleeves of the low- level indication lamps on the MTI, which could cause a short circuit that might result in high voltage being conveyed to the high- and low- level sensors in the wing tanks. This condition could cause the level sensor to heat above acceptable limits, possibly resulting in a fuel tank explosion, and consequent loss of the airplane.
2021-25-08: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AW189 helicopters. This AD was prompted by the determination that certain part-numbered fairings were never introduced into the main rotor (MR) tip lights kit design definition and were not certified for icing conditions. This AD requires replacing affected parts. This AD also prohibits, after modification of the helicopter as required, installing any affected part on any helicopter 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.
2004-12-06: This amendment adopts a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model EC 155 B and B1 helicopters. This action requires inspecting each main rotor blade (blade) for a crack in the blade tip cap mounting bracket (tenon), measuring the vertical clearance between each blade assembly and a straight edge at the blade-to-tip cap junction, and replacing the blade if a crack is found or if the measured distance is not within certain specifications. This amendment is prompted by the discovery of a crack in a tenon. This condition, if not detected, could result in loss of the tip cap, which could lead to severe vibration and loss of control of the helicopter.
2012-12-09: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 717-200 airplanes. This AD was prompted by reports of cracks found on the center section ribs of the horizontal stabilizers. This AD requires repetitive inspections for cracking of the aft face of the left and right rib hinge bearing lugs of the center \n\n((Page 36144)) \n\nsection of the horizontal stabilizer; and crack measurement, repairs, post-repair repetitive inspections, and installation of a new center section rib if necessary. We are issuing this AD to detect and correct cracking in the left and right bearing lugs of the rib hinge spreading at the same time, which could result in failure of both hinge bearing lugs. Failure of the hinge bearing lugs could result in the inability of the horizontal stabilizer to sustain flight loads and thereby reduce the controllability of the airplane.
2012-12-02: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, and Model CL-600-2D24 (Regional Jet Series 900) airplanes. This AD was prompted by reports of a bleed air leak from the high pressure ducts which was not immediately detected by the bleed leak detection system. This AD requires installing new sensing elements in the main landing gear wheel well and the overwing area, protective blankets on the upper surface of the wing box and fuel tubes, and protective shields on the rudder quadrant support-beam in the aft equipment compartment. We are issuing this AD to prevent an undetected bleed [[Page 36130]] air leak which can cause loss of rudder control, can lead to degradation of structural integrity, and could be a potential heat source that can lead to fuel being ignited.
2021-23-06: The FAA is adopting a new airworthiness directive (AD) for various Model 234 and Model CH-47D helicopters. This AD was prompted by two reports of mechanical failures of the longitudinal cyclic trim actuator (LCTA). This AD requires determining the maintenance history, and hours time-in-service (TIS) and number of lift cycles for each LCTA since last overhaul, and then requires initial and repetitive overhauls of each LCTA based on that maintenance and service history. This AD also prohibits installing an LCTA unless it meets certain requirements. Finally, this AD requires reporting certain information to the FAA. The FAA is issuing this AD to address the unsafe condition on these products.
2004-12-10: The FAA is adopting a new airworthiness directive (AD) for certain serial-numbered propeller blades installed in Hamilton Sundstrand Corporation (formerly Hamilton Standard Division) 568F propellers. This AD requires replacement of propeller blades, part numbers (P/Ns) R815505-3 and R815505-4 that have a serial number (SN) of FR1699 to FR20021010, with serviceable blades. This AD results from reports of these composite propeller blades found at inspection, with random areas of missing adhesive under the compression wrap, which exposed the steel tulip part of the blade. We are issuing this AD to prevent propeller blade failure due to corrosion-induced fatigue, which could result in blade separation and possible loss of airplane control.
59-17-01: 59-17-01 WRIGHT: Applies to All TC18DA and TC18EA Series Engines. Compliance required as follows: Engine Model TC18EA2-Not later than October 1, 1959. All other EA Series Models and TC18DA Series-At the first overhaul after October 15, 1959, but not later than March 31, 1960, except TC18DA2, TC18DA3, TC18DA4, TC18EA1, TC18EA3, and TC18EA6 engines not later than July 31, 1960. Instances of propeller shaft cracking through the hydro-oil holes have occurred causing a loss of propeller control. To increase the strength of the propeller shaft and prevent this type of failure, the walls of the hydro-oil holes must be inspected and shotpeened in accordance with the instructions contained in Wright Aeronautical Division Service Bulletins Nos. TC18E-178 or TC18-359.
2012-10-52: We are adopting a new airworthiness directive (AD) for Cessna 206, 207, and 210 airplanes with Hartzell Engine Technologies (HET) turbochargers, part numbers (P/Ns) 406610-0005 and 406610-9005, installed. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires removing the affected turbochargers from service before further flight. This AD was prompted by a report of an HET turbocharger causing an engine in-flight power rollback. We are issuing this AD to prevent turbocharger bearing seizure, failed turbocharger components, and damage to the airplane.
2021-26-11: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd. & Co KG (RRD) RB211 Trent 875-17, 877-17, 884-17, 884B-17, 892-17, 892B-17, and 895-17 model turbofan engines. This AD was prompted by reports of single engine events caused by water contamination, which led to corrosion on the fuel pump that resulted in loss of engine thrust. This AD requires replacing the fuel pump 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.
52-27-02: 52-27-02 DOUGLAS: Applies to Model DC-6 Aircraft (Fuselage Numbers 1 to 166, Inclusive). \n\n\tCompliance required as indicated. \n\n\tThe following inspections and rework pertain to the outboard front spar splice plate, Douglas P/N 4325272 at Station 166 in the area of the inboard nacelle. This special inspection does not apply to splice plates that have been reworked by removing the aft attach tab or to new redesigned splice plates or when Douglas Service Bulletin 532 has been accomplished. \n\n\t1.\tInspection. \n\n\t\tA.\tConduct following inspection as soon as practical but not later than the next 50 hours operation unless already accomplished and continuing thereafter at intervals of regular inspection periods nearest to 500 flying hours from the time of initial inspection until the splice plate is replaced. Using at least an 8-power magnifying glass and/or dye check method or equivalent, make inspections for cracks in the chordwise direction in the area of the milled radius of the aft attach tab of the lower front spar splice plate. Alternate inspection procedures which will provide equivalent safety may be approved. If cracks are found, incorporate the rework of the item 2 before the next scheduled flight. \n\n\t\tB.\tThe above inspection must be continued periodically at intervals not to exceed 400 flying hours on all splice plates that have been reworked as per item 2A until the splice plate is replaced. If a crack is found beyond the stop drill hole prior to the replacement period as indicated in item 2C the splice plate must be replaced before the next scheduled flight. \n\n\t2.\tRework. \n\n\t\tA.\tIf cracks are found less than 1 3/8 inches long, stop drill using a 1/4-inch drill and ream with 17/64-inch reamer. The drill hole center must be located at a distance of 1 3/8 inches from the aft edge of the splice plate in line with the crack. \n\n\t\tB.\tIf cracks are found greater than 1 3/8 inches long, the splice plate must be replaced before the next flight.C.\tSplice plates reworked in accordance with item 2A must be replaced within 1,500 flying hours from time rework is accomplished. \n\n\t(Douglas Service Letter No. 123, dated May 29, 1952, also covers this same subject.)
96-09-10: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Textron Lycoming reciprocating engines, that currently requires replacement of sintered iron impellers in oil pumps. This amendment continues to require replacement of sintered iron impellers, but also requires replacement of aluminum impellers. This amendment is prompted by reports of additional oil pump failures caused by aluminum impellers, which do not have the reliability of the hardened steel impellers. The actions specified by this AD are intended to prevent an oil pump failure due to impeller failure, which could result in an engine failure.
2004-12-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Raytheon Model BAe.125 series 800A, 800A (C-29A), and 800B airplanes; and Model Hawker 800 airplanes, that requires a one-time inspection of certain wire bundles for discrepancies and related corrective action. This action is necessary to find and fix chafing and damage to the wire bundles, which could result in electrical arcing and heat damage in a potential fuel zone and possible fire or explosion in the fuel tank. This action is intended to address the identified unsafe condition.
2021-19-15: The FAA is superseding Airworthiness Directive (AD) 2019-01- 08, which applied to certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. AD 2019-01-08 required modifications for galley mounted attendant seat fittings. This AD was prompted by a report that showed a non-compliance exists on some in-service galley attendant seat fitting installations, and a determination that additional airplanes are subject to the unsafe condition. This AD requires modifications for galley mounted attendant seat fittings. The FAA is issuing this AD to address the unsafe condition on these products.
66-30-02: 66-30-02 BOEING: Amdt. 39-316 Part 39 Federal Register December 13, 1966. Applies to Model 727 Series Airplanes. \n\n\tCompliance required as indicated, unless already accomplished. \n\n\tTo minimize fuselage fire hazards resulting from fuel line ruptures during excessively hard landings involving structural damage, accomplish the following; \n\n\t(a)\tWithin the next 1,500 hours' time in service after the effective date of this AD, remove aluminum fuel lines, P/N 69-16668-1, in the fuselage (three places) located between Body Stations 887 and 1183, and replace with flexible fuel lines, P/N 10-60536-2, in accordance with Boeing Service Bulletin No. 28-26, dated April 27, 1966, or later FAA-approved revision or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\t(b)\tWithin the next 7,000 hours' time in service after the effective date of this AD, reroute the generator electrical leads (three places) and encase in teflon tubing between Fuselage Stations 850 and 1183 in accordance with Boeing Service Bulletin No. 24-30, revised May 18, 1966, or later FAA-approved revision, or an equivalent approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tThis directive effective January 12, 1967.
2021-26-09: The FAA is adopting a new airworthiness directive (AD) for certain Brantly Helicopters Industries U.S.A. Co., Ltd., Model 305 helicopters and Brantly International, Inc., Model B-2, B-2A, and B-2B helicopters. This AD was prompted by a report of a crack in the tail rotor (T/R) hub. This AD requires repetitive inspections of the T/R hub and depending on the results, removing the T/R hub from service. The FAA is issuing this AD to address the unsafe condition on these products.
77-13-17: 77-13-17 MCCAULEY PROPELLERS: Amendment 39-2943. Applies to the following two-bladed and three-bladed constant speed "Non-Feathering" and "Full Feathering" type McCauley propellers, which were modified by Hoosier Aircraft Accessory, Inc., Indianapolis, Indiana during the period of December 8, 1972 thru June 30, 1975. These propellers are installed on, but not limited to the aircraft models listed below. Constant Speed "Non-Feathering" Propellers Model (Note 1) Hub Serial No. (Note 2) Aircraft Model (Note 3) (A) Two Bladed 2A34C22 (*) 713477 Maule M-5-220C; 714270 M-4-180C, S, T D2A34C67 (*) 692205 Cessna R172E, -F, -G, and -H; FR172E, -F, -G, and - H, Maule M-4-210C, -210S, - 210T; M-5-210C (B) Three Bladed D3A32C77 (*) 661184 Cessna P206A, TP206A, 726348 210F, and T210F D3A32C88 (*) 724926 Cessna P206, P206A, - B, -C, -D, -E; Cessna TP206A, -B, - C, -D, -E; TU206F (S/N U20602200 and up) Cessna 210F, -G, -H, - J, -K, -L; T210G, -H, -J, -K, and -L Constant Speed "Full-Feathering" Propellers Model (Note 1) Hub Serial No. (Note 2) Aircraft Model (Note 3) (A) Two Bladed D2AF34C30 (*) 700468 Beech 58, 58A or 701342 2AF34C30 (*) 705241 705242 D2AF34C52 (*) 728611 Cessna 310I 730034 730556 2AF34C55 (*) 682955 Beech 95-55, 95-A55, 684789 95-B55, 95-B55A 697330 95-B55B, 95-C55, 713643 95-C55A, D-55, D- 55A, 726670 E-55, E-55A Series 728131 728141 D2AF34C59 (*) 642020 Cessna 337; 337A, -B, -C, or 723964 -D, -E, and -F Series 2AF34C59 (*) Burns BA42 D2AF34C61 (*) 66394 Cessna 336; 337, 337A, or 675836 -B, -C, -E and -F 2AF34C61 (*) 683257 Series; T337B, -C, -D, 684839 -E and -F Series; F337E, 686708 F337F 691475 727098 736922 741911 745073 750643 D2AF34C71 (*) 685300 Cessna 310P, -Q, -R; 694684 T310P, -Q; 320D, -E and340 D2AF34C81 (*) 651926 Cessna 310J, E310J, 671750 310K, 310L, and 310N 672239 673494 682298 741088 741102 D2AF34C91 (*) 722029 Cessna T337B, T337C, T337D, T337E and T337F; and FT337E, FT337F (B) Three Bladed 3AF34C74 (*) 661086TR Cessna 411, 411A 662363TR 692379 3AF32C75 (*) 702047 Beech 95-C55, 95- C55A, 702051 D55, D55A, E55, and E55A D3AF32C80 (*) 66986 Cessna 310K, -L, and - N or 661000 Colemill Executive 600 3AF34C80 (*) 665633 (STC SA518SO - Cessna 738455 310J, -K, -L, -N 738586 Conversion) 744076 3AF32C87 (*) 68588 Cessna 310P, -Q, -R; 683600 TP310P, -Q, -R; 320D, 683602 -E, -F; 340 685410 Colemill Executive 600 692770 (STC SA518SO Cessna 694218 310I Conversion) 705807 Riley (STC SA1181SW- 710281 Cessna 340 Conversion) 712311 713792 723589 737625 737974 739577 743892 743893744411 746518 748219 3AF34C92 (*) 682034 Cessna 421, 421A, and -B or 682054 3AF32C92 (*) 685899 686191 720868 721301 733370 734880 3AF32C93 722256 Cessna 414 722257 Notes: (*) - Denotes suffix letter(s). Some models have one or more suffix letter designations, others have none. (1)&(2) - Propeller model and hub serial numbers are stamped on the side of the propeller hub. The listing of hub serial numbers refers to specific hub serial numbers not series. In the event a spinner is installed, the spinner should be removed to check the model and hub (S/N) designations. The aircraft's records should likewise be checked to endure that the model and hub serial number coincide with the records. In the event an error is noted, the records should be corrected accordingly. Prior to further flight, spinners should be reinstalled where applicable. (3) - If no listing of aircraft serial numbers is indicated, applies to all applicable serial numbers of a particular aircraft model or series. Compliance required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To preclude the possibility of blade actuating pin failures resulting from using an incorrect actuating pin, or improper rework of the ferrules and installation of the blade actuating pins and washers (i.e., a blind actuating pin hole not tapped to the proper depth can cause stripped threads on the ends of the actuating pin resulting in severe stress and may prevent actuating pin from seating properly on the washer), accomplish the following: A. Disassemble the propeller and inspect the blade actuating pins, washers McCauley Service Bulletins No. 99 dated December 8, 1972, No. 99-1 dated December 14, 1972, No. 99-2 dated April 23, 1973, and No. 99-3 dated August 11, 1975, or later Federal Aviation Administration approved revisions. B. Prior to further flight repair or replace as necessary, any improperly installed blade actuating pins, washers and ferrules, and reassemble the propeller in accordance with McCauley Service Bulletins No. 99 dated December 8, 1972, No. 99-1 dated December 14, 1972, No. 99-2 dated April 23, 1973, No. 99-3 dated August 11, 1975, and Service Manuals 710930 and 720415, or later Federal Aviation Administration approved revisions. C. When the above propellers are released for service, compliance with this Airworthiness Directive shall be noted in the Aircraft's Records. D. The Responsible propeller repair station will notify the Federal Aviation Administration, Chief, Engineering and Manufacturing Branch, AGL-210, 2300 East Devon Avenue, Des Plaines, Illinois 60018, by certified mail of the results of these inspections. The disposition of the affected propeller(s) including the blade and hub serial numbers of the propellers (as received and where applicable, as returned to service) must be reported. (Reporting approved by the Office of Management and Budget under OMB No. 04-R-174.) The manufacturer's specifications and procedures identified in this directive are incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by the directive who have not already received these documents from the manufacturer, may obtain copies upon request to McCauley Accessory Division, Cessna Aircraft Corporation, Box 7, Roosevelt Station, Dayton, Ohio 45417. These documents may also be examined at the Great Lakes Regional Office, 2300 East Devon Avenue, Des Plaines, Illinois 60018, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. A historical file on this airworthiness directive which includes incorporated material in full is maintained by the FAA at its Headquarters in Washington, D.C. and the Great Lakes Region. This amendment becomes effective: July 6, 1977.
2004-12-04: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and A300 B4 series airplanes, that requires modification of the 107VU electronics rack in the avionics compartment to ensure that fluid does not enter the rack. This action is necessary to prevent the loss of electrical power during flight, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
2021-25-04: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd. & Co KG (RRD) Trent 1000 model turbofan engines. This AD was prompted by the manufacturer revising the engine Time Limits Manual (TLM) life limits of certain critical rotating parts and direct accumulation counting (DAC) data files. This AD requires the operator to revise the airworthiness limitations section (ALS) of their existing approved aircraft maintenance program (AMP) by incorporating the revised tasks of the applicable TLM for each affected model turbofan engine, 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.
69-06-05: 69-06-05 FAIRCHILD-HILLER: Amdt. 39-737. Applies to F-27 and FH-227 Type Airplanes Incorporating Lear Siegler (Jack & Heintz) Inverters P/N F35-5 or P/N F45-10 or P/N 40045-000 with Solid State Regulators Lear Siegler Kit P/N 52-000054 (Regulator P/N 51502-000), or Kit P/N 52-000059 (Regulator P/N 51502-001), or Kit P/N 52-000068 (Regulator P/N 51502-00M), or Bendix Type 4B39 Series Regulators. Compliance required within the next 1200 hours time in service after the effective date of this AD unless already accomplished. To prevent hazards associated with an inverter overvoltage condition causing the burnout or erratic operation of required instruments, accomplish the following: (a) Install a.c. overvoltage protection in the electrical output of the above inverter(s) which utilize Lear Siegler solid state regulators, P/N 51502-000, or P/N 51502-001, or P/N 51502-00M, in accordance with Lear Siegler Service Bulletin No. 148-1 dated February 7, 1969, or F-27 aircraftand FH-227 aircraft or later FAA approved revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or equivalent installation approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region. (b) Install a.c. overvoltage protection in the electrical output of the above inverter(s) which utilize Bendix 4B39 Series regulators in accordance with Bendix Service Bulletin No. R220 dated November 15, 1968, or later FAA-approved revision approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region, or equivalent installation, 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 is effective April 15, 1969.
90-23-19: 90-23-19 PRATT & WHITNEY: Amendment 39-6753. Docket No. 90-ANE-11. Applicability: Pratt & Whitney (PW) JT9D-3A/-7/-7A/-7A(SP)/-7AH/-7F/-7H/-7J/-20/-20J/-7R4D/-7R4D1/ -7R4E/-7R4E1/-7R4E4/-7R4H1/-7R4G2 turbofan engines installed on, but not limited to, Boeing 767, Boeing 747, McDonnell Douglas DC10-40, Airbus A300 and Airbus A310 aircraft. Compliance: Required as indicated, unless already accomplished. To prevent failure of the high pressure turbine HPT) stage one rotating air seal, which could result in an uncontained engine failure, accomplish the following: (a) For JT9D-7R4E1 (AI 600 Series)/E4/H1 model engines, remove from service HPT stage one rotating air seal, Part Numbers (P/N) 797576, 797576P48, 793707 and 793707P48, within 60 days from the effective date of this AD, in accordance with Service Bulletin (SB) JT9D-7R4-72-392, Revision 2, dated March 2, 1990. (b) For JT9D-7R4G2 model engines, remove from service HPT stage one rotating air seal, P/N's 797576, 797576P48, 793707 and 793707P48, at the next engine shop visit or within 2,350 cycles in service (CIS) from the effective date of this AD, whichever occurs first, in accordance with SB JT9D-7R4-72-392, Revision 2, dated March 2, 1990. (c) For JT9D-7R4D/D1/E/E1(AI 500 Series) model engines, remove from service HPT stage one rotating air seal, P/N's 797576, 797576P48 and 793707, whose part serial numbers (S/N) are listed in Tables 1-3 inclusive of JT9D SB JT9D-7R4-72-393, Revision 1, dated December 21, 1989, at the next engine shop visit or within 2,450 CIS from the effective date of this AD, whichever occurs first, in accordance with the above noted SB. (d) For JT9D-7R4D/D1/E/E1(AI 500 series) model engines, fluorescent penetrant inspect (FPI) HPT stage one rotating air seal, P/N's 797576, 797576P48 and 793707, whose part S/N's are not listed in Tables 1-3 inclusive of SB JT9D-7R4-72-393, Revision 1, dated December 21, 1989, in accordance with the Accomplishment Instructions, Part B, of the above noted SB, at the next HPT module exposure or within 2,900 CIS after the effective date of this AD, whichever occurs first. Remove from service parts found cracked and replace with a serviceable air seal. Thereafter, reinspect at each HPT module exposure not to exceed 2,900 cycles since last inspection (CSLI), in accordance with the above noted SB. (e) For JT9D-3A/-7/-7A/-7A(SP)/-7AH/-7F/-7H/-7J/-20/-20J model engines, remove from service HPT stage one rotating air seals, P/N's 797576, 797576P48 and 793707, whose part S/N's are listed in Tables 1-3 inclusive of SB 5873, Revision 1, dated December 21, 1989, at the next engine shop visit or within 2,450 CIS after the effective date of this AD, whichever occurs first. (f) For JT9D-3A/-7/-7A/-7A(SP)/-7AH/-7F/-7H/-7J/-20/-20J model engines, FPI HPT stage one rotating air seal, P/N's 797576, 797576P48 and 793707, whose part S/N's are not listed in Tables 1-3 inclusive of PW SB 5873, Revision 1, dated December 21, 1989,in accordance with the Accomplishment Instructions, Part B, of the above noted SB, at the next HPT module exposure or within 2,900 CIS from the effective date of this AD, whichever occurs first. Remove from service parts found cracked and replace with a serviceable air seal. Thereafter, reinspect at each HPT module exposure not to exceed 2,900 CSLI, in accordance with the above noted SB. (g) For the purpose of this AD, an engine shop visit is defined as the induction of an engine into a shop for the conduct of engine maintenance. (h) For the purpose of this AD, HPT module exposure is defined as separation of the M Flange. (i) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (j) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specifiedin this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803. The removal and inspection procedures shall be done in accordance with the following PW documents: Document Page No. Revision Date SB JT9D-7R4-72-392 2 Original Oct. 25, 1989 5, 6, 8, Rev.1 Dec. 21, 1989 9, 10 1, 3, 4, 7 Rev.2 March 2, 1990 SB JT9D-7R4-72-393 2-4 Original Oct. 27, 1989 1, 5 thru 15 Rev. 1 Dec. 21, 1989 SB 5873 2 thru 5 Original Oct. 30, 1989 1, 6, thru 16 Rev. 1 Dec. 20, 1989 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 Pratt & Whitney, Publications Department, P.O. Box 611, Middletown, Connecticut 06457. Copies may be inspected at the Regional Rules Docket, Office of the Assistant Chief Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Room 311, Burlington, Massachusetts 01803, or at the Office of the Federal Register, 1100 L Street NW, Room 8301, Washington, D.C. 20591. This amendment (39-6753, AD 90-23-19) becomes effective on November 23, 1990.