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98-25-10 R1: This amendment revises an existing airworthiness directive (AD), applicable to Aircraft Belts, Inc. Model CS, CT, FM, FN, GK, GL, JD, JE, JT, JU, MD, ME, MM, MN, NB, PM, PN, RG, and RH seat restraint systems installed on, but not limited to, Beech Aircraft Corp., Bell Helicopter Textron, Inc., Cessna Aircraft Co., Dassault Aviation, Eurocopter Deutschland, Eurocopter France, Gulfstream Aerospace, Learjet Corp., Lockheed Aircraft Corp., and Piper Aircraft Corp. aircraft, that currently requires inspecting to ensure the locking mechanism is engaging properly and replacing the buckle-half of the seat restraint system, if necessary. This amendment will allow an owner/operator (pilot) to determine if the locking mechanism is engaging properly and will require replacing the buckle-half of the seat restraint system, if necessary. This amendment is prompted by a determination made by the FAA that pilots may perform the one-time check of the locking mechanism and that only affectedseat restraint systems manufactured between March 1997 and November 1998 must be checked. The actions specified by this AD are intended to prevent failure of the seat restraint system due to the buckle assembly locking mechanism not engaging properly, which could result in the seat restraint system failing to properly secure the occupant during turbulence or landing.
47-16-03: 47-16-03 TAYLORCRAFT: (Was Mandatory Note 11 of AD-700-1: Mandatory Note 12 of AD-699-1; and Mandatory Note 13 of AD-696-3.) Applies to All Models BC, BF, and BL Series Aircraft. Compliance required immediately. Inspect wing strut attachment fittings on lower fuselage longerons for cracks or evidence of poor weld. If cracks or defects are found, the fitting should be replaced or reinforced.
2014-13-03: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) RB211 Trent 553-61, 553A2-61, 556-61, 556A2-61, 556B-61, 556B2-61, 560-61, and 560A2-61 turbofan engines. We are issuing this AD to address, through an update to the electronic engine control (EEC) software, multiple risks of uncontained engine failure and damage to the airplane.
99-25-13: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 777-200 and -300 series airplanes. This action requires revising the Limitations Section of the Airplane Flight Manual to prohibit the dispatch of certain airplanes under certain conditions. This amendment also requires repetitive inspections to ensure correct operation of the backup generators; and, for certain airplanes, a one-time inspection to detect damage of the engine external gearbox; and corrective actions, if necessary. This amendment is prompted by reports of inflight shutdowns due to sheared backup generator shafts. The actions specified in this AD are intended to prohibit the dispatch of an airplane with an engine-mounted backup generator having a sheared shaft; and to detect and correct damage to the engine, which could result in inflight shutdowns.
99-25-07: This amendment adopts a new airworthiness directive (AD) that is applicable to certain BFGoodrich main brake assemblies as installed on Airbus Model A319 and A320 series airplanes. This action requires a one time inspection of the wear indicator pins to determine the level of wear of the main brake assemblies of the main landing gear (MLG), and corrective actions, if necessary. This action also requires modification of the main brake assemblies of the MLG, and incorporation of specified wear limits into the maintenance inspection program. This amendment is prompted by in-service reports of brake deterioration caused by thermal oxidation of the carbon disks of certain BFGoodrich main brake assemblies. The actions specified in this AD are intended to prevent thermal oxidation of the main brake assemblies, which could result in deterioration of the MLG brakes, and consequent reduced braking performance.
94-03-11: 94-03-11 HARTZELL PROPELLER INC.: Amendment 39-8818. Docket 94-ANE-06. Applicability: Hartzell Propeller Inc. HC-B4 series propellers, except those propellers installed on Mitsubishi MU-2B-26A, -36A, -40, and -60 aircraft. The affected propellers are installed on but not limited to the following aircraft: Beech F90 King Air, A100 and A100A King Air, B100 King Air; Construcciones Aeronauticas, SA (CASA) C-212-CB, -CC, and -CF; Dehavilland Heron--Saunders conversion ST-27B; Dornier DO228-100, -101, -200, -201, -202, -212; Embraer EMB-121A1 Xingu; Fairchild SA226-TB Merlin IIIB; Let L-410A; and Shorts SC-7 series 3, variant 200. NOTE: This airworthiness directive (AD) does not contain an exhaustive list of aircraft which utilize these propellers. Other Type Certificated models may not be included in the list, and other aircraft may use the affected propeller models through, for example, installation approvals made by Supplemental Type Certificate or FAA Form 337 "Major Repair and Alteration." It is the responsibility of the owner, operator, or person returning the aircraft to service to determine if an aircraft has an affected propeller. Compliance: Required as indicated, unless accomplished previously. To prevent possible fatigue cracks in propeller hub arm assemblies progressing to failure, resulting in departure of the hub arm and blade, that may result in engine separation and subsequent loss of aircraft control, accomplish the following: (a) For each Hartzell Propeller Inc. HC-B4 series propeller currently installed on an aircraft other than Mitsubishi MU-2B series aircraft, determine if the propeller hub arm assembly has ever seen service on a Mitsubishi MU-2B series aircraft prior to performing the inspections required by the compliance schedule contained in paragraph (b) of this AD: (1) Determine if the currently installed propeller hub assembly matches a serial number (S/N) in Table 1 of Hartzell Propeller Inc. Alert Service Bulletin (ASB) No. A186, dated January 25, 1994; and (2) If the currently installed propeller hub assembly's S/N is not listed in Table 1 of Hartzell Propeller Inc. ASB No. A186, dated January 25, 1994, and an aircraft and propeller maintenance record search confirms the currently installed propeller hub assembly has not been previously installed on a Mitsubishi MU-2B series aircraft, or the service history cannot be determined, no further action is required. (3) If the record search reveals that the S/N of the currently installed propeller hub arm assembly is listed in Table 1 of Hartzell Propeller Inc. ASB No. A186, dated January 25, 1994, or the propeller hub arm assembly was installed previously on a Mitsubishi MU-2B series aircraft, remove the propeller hub arm assembly in accordance with the compliance schedule listed in paragraph (b) of this AD, and inspect and rework in accordance with the requirements of paragraph (c) of this AD. (b) For propeller hub arm assemblies identified in paragraph (a)(3) of this AD, remove from service in accordance with the following schedule: Time in Service Since New on the Effective Date of this AD (TSN) or Assemblies That Have Experienced a Blade Strike Compliance Required Greater than or equal to 3,000 hours TSN l Within the next 300 hours time in service (TIS), the next scheduled overhaul, or 24 calendar months after the effective date of this AD, whichever occurs first. Less than 3,000 hours Prior to the accumulation of 3,300 hours TSN, the TSN next scheduled overhaul, or 24 calendar months after the effective date of this AD, whichever occurs first. Regardless of TSN, propeller hub arm assemblies that have experienced a blade strike prior to the effective date of this AD. See paragraph (e) of this AD for the definition of blade strike. Within the next 100 hours TIS, or 2 calendar months after the effective date of this AD, whichever occurs first. Regardless of TSN, propeller hub arm . assemblies that experience a blade strike after the effective date of this AD. See paragraph (e) of this AD for the definition of a blade strike Prior to further flight (c) Remove affected propeller hub arm assemblies from the aircraft and return to Hartzell Service Center, 5465 West State Route 185, Piqua, OH 45356-2634 USA, telephone (513) 778-4205, for inspection and specified rework, in accordance with Hartzell Propeller Inc. ASB No. A186, dated January 25, 1994. (d) Reinstall serviceable propeller hub arm assemblies that had the hub arm bores inspected and reworked, as necessary, pilot tubes replaced, and were marked at the end of the hub arm assembly S/N with a suffix letter "M" in accordance with Hartzell Propeller Inc. ASB No. A186, dated January 25, 1994. (e) A blade strike is defined as a propeller having any blade or blades that have been bent beyond serviceable limits in accordance with Hartzell Propeller Inc. Service Letter (SL) 61S, dated December 10,1993. (f) The "calendar month" compliance time stated in this AD allows the performance of the required action prior to the last day of the month in which compliance is required. NOTE: For example, if action is required 2 calendar months from April 28, 1994, the required actions are to be performed not later than June 30, 1994. (g) 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, Chicago Aircraft Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Chicago Aircraft Certification Office. NOTE 1: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Chicago Aircraft Certification Office. NOTE 2: Although Hartzell Service Center is presently the only FAA-approved repair facility authorized to conduct the requirements of this AD, other facilities may be authorized through the alternative method of compliance procedure in paragraph (g) of this AD. (h) Except when propeller hub arm assemblies experience a blade strike after the effective date of this AD, special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the aircraft to a location where the requirements of this AD can be accomplished. (i) The removal, inspection, and rework shall be done in accordance with the following service documents: Document No. Pages Revision Date Hartzell ASB No. A186 1-4 Original January 25, 1994 Total pages: 4. 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 Hartzell Propeller Inc., One Propeller Place, Piqua, OH 45356-2634. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (j) This amendment becomes effective on February 28, 1994.
93-25-17: 93-25-17 GENERAL ELECTRIC: Amendment 39-8781. Docket No. 92-ANE-08. Applicability: General Electric (GE) Models CT7-5A2, -7A, and -9C Turboprop Engines; and Models CT7-2A, and -6 Turboshaft Engines, incorporating gas generator turbine (GGT) disks and cooling plates, as listed by Part Number (P/N) and Serial Number (S/N) in GE CT7 Turboprop Service Bulletin (SB) A72-252, dated August 31, 1990; GE CT7 Turboshaft SB A72-17, and GE CT7 Turboshaft SB A72-18, both dated September 10, 1990, installed on, but not limited to, Saab 340A, Casa CN235-10, Bell 214ST, and European Helicopter Industries EH101. Compliance: Required as indicated, unless accomplished previously. To prevent fatigue cracks that can result in uncontained engine failure, accomplish the following: (a) Remove from service the affected GE Model(s) CT7-5A2, -7A, and -9C engines GGT rotor stage 1 and 2 disks, and stage 2 forward and aft cooling plates, prior to exceeding the "Max total allowable cycles"; as listed in GE CT7 Turboprop SB A72-252, dated August 31, 1990, and replace with serviceable parts. (b) Remove from service the affected GE Model(s) CT7-6 engine GGT rotor stage 1 disk and stage 2 forward cooling plate prior to exceeding the "Max total allowable cycles"; as listed in GE CT7 Turboprop SB A72-17, dated September 10, 1990, and replace with serviceable parts. (c) Remove from service the affected GE Model(s) CT7-2A engine GGT rotor stage 2 disk and stage 2 forward cooling plate prior to exceeding the "Max total allowable cycles"; as listed in GE CT7 Turboshaft SB A72-18, dated September 10, 1990, and replace with serviceable parts. (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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, EngineCertification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the Engine Certification Office. (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 removals and replacements of the affected rotor stage disks and cooling plates shall be done in accordance with the following service bulletins: DOCUMENT NO. PAGE NO. ISSUE DATE GE CT7 Turboprop SB A72-252 1-13 Original Aug 31, 1990 TOTAL PGS: 13 GE CT7 Turboshaft SB A72-17 1-4 Original Sep 10, 1990 TOTAL PGS: 4 GE CT7 Turboshaft SB A72-18 1-4 Original Sep 10, 1990 TOTAL PGS: 4 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 General Electric Aircraft Engines, 1000 Western Avenue, Lynn, Massachusetts 01910. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, Attn: Rules Docket No. 92-ANE-08, 12 New England Executive Park, Burlington, Massachusetts; or at the Office of the Federal Register, 800 North Capitol Street NW., suite 700, Washington, DC. (g) This amendment becomes effective on February 2, 1994.
90-25-13: 90-25-13 AEROSPATIALE (FORMERLY SUD AVIATION/SUD-SERVICE): Amendment 39-6820. Docket No. 90-NM-159-AD. Applicability: All Caravelle SE 210 Model I, III, and VIR series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To detect cracks in the rear spar upper cap at Rib 49 and to prevent reduced structural integrity of the wings, accomplish the following: A. Prior to the accumulation of 25,000 landings, or within 120 days after the effective date of this AD, whichever occurs later, perform an eddy current rototest inspection of hole No. 1 (left and right wings) at the level of the rear spar upper cap (angle extrusion) and the splice under Rib 49, in accordance with Aerospatiale Service Bulletin 57-69, dated March 12, 1990. If no crack is detected in hole No. 1, the airplane may be returned to service. B. If a crack is detected in the angle extrusion for hole No. 1, accomplish the following in accordance with Aerospatiale Service Bulletin 57-69, dated March 12, 1990: 1. Prior to further flight, repair the crack and perform an eddy current rototest inspection of holes No. 2 and 3 (left and right wings), in accordance with the service bulletin. 2. If no crack is found in holes No. 2 and 3, the airplane may be returned to service. Repeat the eddy current rototest inspection of hole No. 2 at intervals not to exceed 1,500 landings in accordance with the service bulletin. 3. If a crack is detected in holes No. 2 or 3, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. C. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM- 113, FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Standardization Branch, ANM-113, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Standardization Branch, ANM-113. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington 98055-4056. This amendment (39-6820, AD 90-25-13) becomes effective on January 7, 1991.
91-14-12: 91-14-12 BRITISH AEROSPACE: Amendment 39-7053. Docket No. 91-NM-44-AD. Applicability: Model HS.125-600A and BH.125-600A series airplanes (Post Modification 252475) and Model HS.125-700A series airplanes (Post Modification 252509); as listed in British Aerospace Service Bulletin 24-279-3255A, dated November 16, 1990; certificated in any category. Compliance: Required within 160 days after the effective date of this AD, unless previously accomplished. To prevent loss of the standby constant frequency power system which provides the necessary back-up capability when the primary power system fails, accomplish the following: A. Install a partial cover above the standby inverter "TF" located between frames 22 and 23 LH if the converter is installed as depicted on pages 5-6 of the service bulletin, in accordance with British Aerospace Service Bulletin 24-279-3255A, dated November 16, 1990. B. An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. D. The installation requirements shall be done in accordance with British Aerospace Service Bulletin 24-279-3255A, dated November 16, 1990. 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-7053, AD 91-14-12) becomes effective on August 6, 1991.
93-12-02: 93-12-02 SAAB-SCANIA: Amendment 39-8607. Docket 93-NM-02-AD. Applicability: Model SAAB SF340A series airplanes, serial numbers 004 through 159, inclusive; Model SAAB 340B series airplanes, serial numbers 160 through 252, inclusive, and 254 through 258, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the fuselage, accomplish the following: (a) Within 3,000 hours time-in-service after the effective date of this AD, install an additional protective shield between the existing heat protection and the air cycle machine, in accordance with SAAB 340 Service Bulletin SAAB 340-53-028, dated August 20, 1992. (b) 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 theirrequests 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. (c) 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. (d) The installation shall be done in accordance with SAAB 340 Service Bulletin SAAB 340-53-028, dated August 20, 1992. 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 SAAB-SCANIA AB, SAAB Aircraft Product Support, S-581.88, Linkoping, Sweden. 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. (e) This amendment becomes effective on July 22, 1993.