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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.
2004-11-13: The FAA is superseding an existing airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. That AD currently requires a one-time general visual inspection to determine the part number and serial number of both main landing gear (MLG) sliding tubes, and related investigative and corrective actions if necessary. This amendment adds an additional inspection to determine only the serial number of the MLG sliding tubes. This AD is prompted by a report that the field of MLG sliding tubes subject to the identified unsafe condition has expanded. We are issuing this AD to detect and correct cracking in an MLG sliding tube, which could result in failure of the sliding tube, loss of one axle, and consequent reduced controllability of the airplane. DATES: Effective June 23, 2004. The incorporation by reference of Airbus All Operators Telex A320- 32A1273, Revision 01, dated May 6, 2004, listed in the AD is approved by the Director of the Federal Register as of June 23, 2004. On April 14, 2004 (69 FR 16475, March 30, 2004), the Director of the Federal Register approved the incorporation by reference of Airbus All Operators Telex A320-32A1273, dated February 5, 2004. We must receive any comments on this AD by August 9, 2004.
2021-24-15: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Canada Limited Model 206L-1, 206L-3, and 206L-4 helicopters with certain Air Comm Corporation air conditioning systems installed. This AD was prompted by reports of damage to the drive ring spline teeth and the mating spline teeth. This AD requires visually inspecting the drive ring spline teeth and the mating area spline teeth on the oil cooler blower shaft for signs of deformation and fretting and depending on the results of the inspection, removing certain parts from service. This AD also requires reinstalling certain parts, applying torque, and aligning certain bolt holes. The FAA is issuing this AD to address the unsafe condition on these products.
2021-23-22: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB139 and AW139 helicopters. This AD was prompted by reports of failed main rotor (MR) dampers. This AD requires various inspections of certain MR dampers, as specified in a European Aviation Safety Agency (now 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.
58-02-01: 58-02-01 BELL: Applies to All Model 47J Helicopters, Using Main Rotor Blade P/N 47- 110-401-7, -9 and -11. Due to the possibility of a faulty bond between the butt plate laminates and the wood portion of the blade, causing a subsequent separation of the subject parts with possible catastrophic results, the following mandatory inspection is required: 1. Inspect butt plate laminates for indication of bond separation by grasping blade at tip and coning blade downward slightly after static stop is contacted, then coning blade upward to extent that tip is above level line of yoke. If separation is found no repair is allowed, remove blades and notify Bell Helicopter Corporation. Inspection required after each refueling until blades accumulate a total of 50 hours flight time and then daily thereafter. 2. Inspect on one-time basis butt plate laminates for bonding voids by tapping lightly completely around exposed surface of each laminate with a four or six inch wrench. Each laminate will have a different sound; however, an obvious variation in sound on an individual laminate tends to indicate a void. If void indicated, notify Bell Helicopter Corporation immediately. This supersedes AD 58-01-02.
2004-11-05: This amendment adopts a new airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters that requires inspecting the fuel transfer line and air exhaust duct for chafing, inspecting the air exhaust duct for a hole, and if necessary, repositioning the air exhaust duct to achieve the minimum clearances. This amendment is prompted by a report of damage to the fuel transfer line due to wear associated with vibrations and chafing of the fuel transfer line and the air exhaust duct. The actions specified by this AD are intended to detect chafing wear of the air exhaust duct and the fuel transfer line, which could result in a hole in the fuel transfer line, fuel leaking into the engine compartment and creating a fire hazard that could lead to a fire and a subsequent forced landing.
2012-10-13: We are superseding an existing airworthiness directive (AD) for certain Continental Motors, Inc. (CMI) models TSIO-520, TSIO-550-K, TSIOF-550K, and IO-550-N series reciprocating engines with new or rebuilt CMI starter adapters installed between January 1, 2011 and November 20, 2011. That AD currently requires replacing affected CMI starter adapters with starter adapters eligible for installation. This AD requires the same actions, but to an expanded population of reciprocating engines. This AD was prompted by two additional reports received of fractures in starter adapter gear shafts in certain additional part number (P/N) CMI starter adapters since we issued the existing AD. We are issuing this AD to prevent starter adapter gear shaft failure which could cause oil scavenge pump failure and engine in-flight shutdown.
2021-24-08: The FAA is superseding Airworthiness Directive (AD) 2021-04- 21, which applies to certain Airbus Helicopters Model EC120B helicopters. AD 2021-04-21 required an inspection of the attachment bolts of the main rotor (MR) hub scissors assembly for discrepancies and repair if necessary; part marking of the attachment bolts of the MR hub scissors assembly; and repetitive inspections of the part marking of the attachment bolts, and repair if necessary. This AD continues to require the actions in AD 2021-04-21; and also requires part marking of the washer, scissor branch, and mast ring of the corresponding nut side, and repetitive inspections of the additional part markings and repair if necessary; as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD was prompted by a report of broken and bent attachment bolts of the MR hub scissors assembly and a determination that additional part markings of the washer, scissor branch, and mast ring of the corresponding nut side, and repetitive inspections of those part markings, are necessary to detect any rotation. The FAA is issuing this AD to address the unsafe condition on these products.
58-17-02: 58-17-02 CURTISS-WRIGHT: Applies to all C-46 Series aircraft including the Models C-46R and C-46/CW20-T aircraft. Compliance required as noted. Due to recurrent fatigue cracking on the horizontal tail surfaces, the following inspections must be accomplished: 1. Conduct a daily visual external inspection of the horizontal tail surfaces for cracks with especial reference to cracks developing in the skin and ribs in the area of the elevator balance weights and the elevator hinge cutouts. 2. A detailed visual inspection of the horizontal tail surfaces must be conducted at intervals not to exceed 100 hours' time in service. Particular attention should be paid to cracks developing in the area of the balance weights on the elevator, elevator nose ribs, elevator main spar, and elevator and stabilizer hinge ribs. 3. Any cracks found must be repaired in accordance with the structural repair manual or other approved repair method prior to the next flight. Stop-drilling of cracks is not considered a repair but may form part of a repair. To facilitate inspection, the horizontal stabilizer may be modified in accordance with L.B. Smith Aircraft Corporation Drawing No. 5.040.02, or approved equivalent. To provide access to the elevator interiors for visual inspection, access holes may be added in the elevator skin as shown on Riddle Airlines Incorporated Service Bulletin No. RSB-C- 46-8. Revised July 11, 1961.
2004-11-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F.28 Mark 0070 series airplanes, that requires inspection of cables installed on certain contactors in the electrical power center (EPC) for proper installation of wires, and reinstallation of wires if necessary. These actions are necessary to prevent a short circuit in the EPC, possibly leading to a fire in the main cabin and damage to the airplane, or injury to passengers and flightcrew. These actions are intended to address the identified unsafe condition.