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2001-16-16: This amendment adopts a new airworthiness directive (AD) that is applicable to all Airbus Model A330 and A340 series airplanes. This action requires a one-time inspection to detect cracking of the bogie beams of the main landing gear (MLG), and follow-on actions, if necessary. This action is necessary to detect and correct cracking of the MLG bogie beams, which could result in failure of the beams and consequent loss of the landing gear wheels and brakes, and structural damage to the MLG strut and airframe. This action is intended to address the identified unsafe condition.
2016-26-02: 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, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by a determination that the protective polyurethane tapes applied to the upper surfaces of the aluminum and titanium floor structural members may overhang the profiles of the floor structural parts and may allow fire propagation below the floor structure. This AD requires an inspection of the polyurethane protective tapes installed on the floor structure for excess tape or incorrect tape installation, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
81-16-08 R3: 81-16-08 R3 GATES LEARJET: Amendment 39-4184 as amended by Amendment 39-4295 and 39-4338 is further amended by Amendment 39-4546. Applies to the following models and serial number airplanes certificated in any category: MODELS SERIAL NUMBERS LEARJET AFM DESIGNATION 24E, 24F 350, 352, 353, 354, 356, and subsequent 24-350, 24-352, 24-353, 24-354, 24-356 and subsequent 25D, 25F 206 thru 336 338 thru 341 25-206 thru 25-336, 25-338 thru 25-341 COMPLIANCE: Required as indicated, unless previously accomplished. To assure that the crew is provided with limitations for the safe operation of the airplane and to reduce the possibility of an unsafe condition resulting from a system's malfunction, accomplish the following: A) Before further flight, insert the following information in the FAA Approved Airplane Flight Manual and operate the airplane in accordance with these limitations: 1. In Section 1, LIMITATIONS, adjacent to MAXIMUM OPERATING ALTITUDE:a. Delete any procedures relative to maximum operation altitudes of 51,000 feet. b. Add the following limitation for Model 25D/F: Aircraft 25-230 and subsequent: "The maximum operating altitude is 45,000 feet. This is the highest altitude for which acceptable flight characteristics and systems operation have been demonstrated." c. Add the following limitation for Model 24E: Aircraft 24-350, 24-352 and subsequent, except 24-355: "The maximum operating altitude is 45,000 feet. This is the highest altitude for which acceptable flight characteristics and systems operation have been demonstrated." d. Add the following limitation for Model 24F: Aircraft 24-350 and subsequent when CJ610-8A engines are installed: "The maximum operating altitude is 45,000 feet. This is the highest altitude for which acceptable flight characteristics and systems operation have been demonstrated." B) In order to comply with the requirements of paragraph A) of this Airworthiness Directive, this AD, or a duplicate thereof, may be used as a temporary amendment to the Airplane Flight Manual and carried in the aircraft as part of the Airplane Flight Manual until replaced by revisions to the Airplane Flight Manual provided by the manufacturer and approved by the FAA. The Airplane Flight Manual changes required by paragraph A) of this AD may be accomplished by the holder of at least a private pilot certificate issued under Part 61 of the Federal Aviation Regulations on any airplane owned or operated by that person who must make the prescribed entry in the Airplane Maintenance Records indicating compliance with paragraph A) of this AD. C) Prior to accomplishing the modification required by paragraph D) of this AD, contact the FAA office noted in paragraph F) if any modification or alteration has been performed on the affected airplane for further instruction relative to the compatibility of the modification of this AD. D) On or before May 31, 1982, accomplish the following requirements of this paragraph at an FAA certificated maintenance repair agency. However, the modification and inspection of the horizontal stabilizer trim actuator as required in the airplane modification kits referenced in subparagraph 1 below may be performed by another FAA certificated repair agency utilizing qualified technicians who must have recent accessory overhaul experience performing the overhaul and test of the Gates Learjet Horizontal Stabilizer Trim Actuator with the necessary shop equipment (Attachment I hereto) as referenced in Learjet Repair Manual Number 1711-9, or the equivalent equipment. 1. Modify-Learjet Model 25D and 25F flight control systems, stall warning system and control wheel in accordance with Gates Learjet Airplane Modification Kits AMK 81- 7, AMK 81-8 and AMK 80-13, Change 3, respectively. 2. Insert in the appropriate sections of the existing Airplane Flight Manual (AFM), the FAA-approved temporary Airplane Flight Manual Change dated June 8, 1981, or equivalent permanent AFM revision pertaining to procedures required as a result of the modification of the flight control system in accordance with Airplane Modification Kit AMK 81- 7 and delete superseded AFM revisions previously required by paragraphs A)2, A)5 and A)6 of AD 80-19-11. E) Operators of Model 24E, and 24F, S/N 350, 352, 353, 354, 356, and subsequent, desiring to remove the 45,000 feet limitation of paragraph A), above, may do so by accomplishing the following requirements of this paragraph at a FAA certified maintenance repair agency. However, the modification and inspection of the horizontal stabilizer trim actuator as required in the airplane modification kits referenced in subparagraph 1 below may be performed by another FAA certificated repair agency utilizing qualified technicians who must have recent accessory overhaul experience performing the overhaul and test of the Gates Learjet Horizontal Stabilizer Trim Actuator with the necessary shop equipment (Attachment I hereto) as referenced in Learjet Repair Manual Number 1711-9, or the equivalent equipment. 1. Install AMK 82-6, Engine Stall Warning System, and concurrently required kits called out in "PARTS REQUIRED," namely: AMK 81-13, Horizontal Stabilizer Trim and Autopilot Improvement, AMK 82-4 Autopilot Pitch Nose Down Limiter, and AAK 82- 5 Autopilot Roll Rate Limiter. 2. Incorporate FAA approved Airplane Flight Manual (AFM) Change 9 for Model 24E and Change 7 for Model 24F, which supersedes AFM revisions previously required by paragraph A), above, and delete superseded AFM revisions previously required by paragraphs A)2, A)5, and A)6 of AD 80-19-11. 3. Insert FAA approved AFM Supplement AFMS: W1018, which supersedes previous AFM supplements for FC-110 autopilot. F) Operators of Model 25D and 25F, S/N 230 thru 341, and 343 thru 362, desiring to remove the 45,000 feet limitation of paragraph A), above, may do so by accomplishingthe following requirements at an FAA certificated maintenance repair agency 1. Install AMK 81-12 Engine Stall Warning System, and concurrently required kits called out in "PARTS REQUIRED," namely: AMK 82-4 Autopilot pitch nose down limiter and AAK 82-5 Autopilot Roll Rate Limiter. 2. Incorporate FAA approved Airplane Flight Manual (AFM) Change 8 to the FAA approved Airplane Flight Manual which supersedes AFM revisions previously required by paragraph A), above. 3. Insert FAA approved AFM Supplement AFMS: WI008, Change 1, which supersedes previous AFM supplements for FC-110 autopilot. G) The modifications described above have been incorporated by the manufacturer on airplanes Model 25D and 25F, S/N 342, 363, and subsequent. H) Airplanes may be flown in accordance with FAR 21.197 to a location where modifications required by this AD can be accomplished. I) Any equivalent method of compliance with this AD must be approved by the Manager, Wichita AircraftCertification Office, FAA, Central Region, Room 238, Terminal Building No. 2299, Mid-Continent Airport, Wichita, Kansas 67209. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request from Gates Learjet corporation, P.O. Box 7707, Wichita, Kansas 67277. These documents may also be examined at FAA, Central Region, Wichita Aircraft Certification Office, Room 238, Terminal Building 2299, Mid-Continent Airport, Wichita, Kansas 67209. Amendment 39-4184 became effective on July 31, 1981. Amendment 39-4295 became effective January 21, 1982. Amendment 39-4338 became effective on February 27, 1982. This Amendment 39-4546 becomes effective February 7, 1983 ATTACHMENT I The stabilizer actuator test stand (P/NST-00463) is used to functionally test the stabilizer actuator after overhaul. The physical structure of the test stand must be capable of withstanding a minimum load of 2500 lbs. without any bending or deformation. The stabilizer actuator is vertically mounted on the test stand with one end stationary and the other end movable through a hydraulic actuator. The test stand consists of the following components a. Hydraulic Actuator - The hydraulic actuator is capable of applying a regulated load of 0 to 2500 lbs. on the stabilizer actuator during the entire extend or retract cycles. b. Hydraulic Pressure Regulator - The pressure regulator is used to select hydraulic pressures applied to the stabilizer actuator during the functional test. c. Hydraulic Pressure Gauge - The hydraulic pressure gauge is used to monitor hydraulic pressure applied to the stabilizer actuator. The gauge must be certified at least monthly. d. Digital Position Readout - The digital position readoutindicator is used to monitor the travel of the stabilizer actuator. Signals to the indicator are picked up from a rigid mounted linear potentiometer and movable wiper attached to the hydraulic actuator. The digital readout is accurate to 1/1000th of an inch. e. Linear Scale - A Linear scale, graduated in 100th of an inch, is permanently mounted on the test stand to verify the digital readout. A tool of known length is used to verify the linear scale and digital readout before the stabilizer actuator functional test is performed. The tool length must be certified at least yearly. f. Lapse Timer - A lapse timer is coupled to the control switches and the stabilizer actuator to monitor travel time during the extend and retract cycles. The lapse timer must measure seconds and be accurate to 1/100th of a second. g. Trim Controller - The trim controller is used to simulate two-speed input to the stabilizer actuator primary motor. The trim controller part number is EM 2079-6.h. Pe-Select Timer - The pre-select timer is used to check stabilizer actuator travel vs. time, voltage and amperage inputs in accordance with the functional test. i. Power Supply - The power supply is variable through 0-30 volts DC and 0-30 amperes DC. j. DC Voltmeter - The DC voltmeter must be capable of measuring 0-30 volts DC and must be certified at least yearly. The voltmeter is used to monitor the voltage inputs to the stabilizer actuator in accordance with the functional test. k. DC Ammeter - The DC ammeter must be capable of measuring 0-30 amperes DC and must be certified at least yearly. The ammeter is used to monitor the amperes inputs to the stabilizer actuator in accordance with the functional test. l. Millivolt Meter - The millivolt meter is used to monitor the stabilizer actuator linear potentiometer for a smooth and steady signal output. The meter is 0-50 volts graduated in 100 mv increments. m. Switches - Necessary switches installed to operatethe stabilizer actuator primary and secondary motors to extend or retract. n. A digital or Simpson 260 meter, not a part of the test stand, is used to verify the resistance of the stabilizer actuator linear potentiometer. The digital or Simpson 260 meter must be certified at least every 90 working days.
2010-24-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD requires a one-time visual inspection of the No. 3 bearing oil pressure tube, part number (P/N) 51J041-01, P/N 50J604-01, or P/N 50J924-01. Tubes that are found cracked or repaired must be removed from service. This AD also prohibits repaired tubes from being installed. This AD results from one report of a repaired No. 3 bearing oil tube that caused an engine in-flight shutdown, seven reports of repaired No. 3 bearing oil pressure tubes found cracked that led to unscheduled engine removals, and one report of a test cell event from a repaired tube that cracked. We are issuing this AD to prevent cracking of No. 3 bearing oil pressure tubes, which could result in internal oil fire, failure of the high-pressure turbine (HPT) disks, uncontained engine failure, and damage to the airplane.
2001-17-13: This amendment supersedes Airworthiness Directive (AD) 2001-08-01, which applies to certain JanAero Devices (JanAero) 14D11 and 23D04 series fuel regulator shutoff valves used with certain JanAero combustion heaters that are installed on aircraft. AD 2001-08-01 currently requires you to visually inspect and pressure test these fuel regulator shutoff valves for leaks, and, if leaks are found, replace the fuel regulator shutoff valve. Numerous reports of fuel regulator shutoff valves leaking fuel caused the Federal Aviation Administration (FAA) to issue AD 2001-08-01. This amendment retains the actions of AD 2001-08-01, except only the visual inspection or the pressure test will be required instead of both. This amendment also specifically calls out the fuel regulator shutoff valves by part number instead of series, includes provisions for disabling the heater as an alternative method of compliance, and makes other minor clarifying revisions and additions to the AD. The actionsspecified by this AD are intended to eliminate or severely reduce the potential for fuel leakage in aircraft with these combustion heaters, which could result in an aircraft fire with consequent damage or destruction. The Director of the Federal Register previously approved the incorporation by reference of JanAero Devices Service Bulletin No. A-107, dated January 8, 2001, as of May 10, 2001 (66 FR 19720, April 17, 2001). The FAA must receive any comments on this rule on or before October 5, 2001.
2016-25-13: We are superseding airworthiness directive (AD) 2016-04-12, that applies to certain Safran Helicopter Engines, S.A. (formerly Turbomeca S.A.) Arriel 2B, 2B1, 2C, 2C1, 2C2, 2D, 2E, 2S1, and 2S2 turboshaft engines. AD 2016-04-12 required spectrometric oil analysis (SOA) inspection of the engine accessory gearbox (AGB), and, depending on the results, removal of the engine AGB. This AD requires initial and repetitive wear inspections of the engine AGB cover. This AD was prompted by a report of an uncommanded in-flight shutdown (IFSD) of an Arriel 2S2 engine caused by rupture of the 41-tooth gear, which forms part of the bevel gear in the engine AGB. We are issuing this AD to correct the unsafe condition on these products.
92-06-08: 92-06-08 GULFSTREAM AMERICAN: Amendment 39-8188; Docket No. 91-CE-66-AD. Applicability: Model GA-7 airplanes (serial numbers GA7-0001 through GA7-0115), certificated in any category. Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent elevator binding and loss of pitch control, which could result in loss of control of the airplane, accomplish the following: (a) Dye penetrant inspect the elevator spar between stabilizer station 41.0 and 45.0 for cracks by accomplishing paragraphs A-1, A-2, A-3, B-1, B-2, and B-3 of the MODIFICATION INSTRUCTIONS in the instructions for GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 1991. (1) If cracks are found that extend inboard from station 41.0, outboard of station 45.0, or into the spar caps, prior to further flight, replace the elevator and accomplish the following: (i) Install Service Kit No. 12 by accomplishing paragraphs B-5 through B-20 of the MODIFICATION INSTRUCTIONS in the instructions for GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 1991. (ii) Balance the new elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-1-1. (iii) Install the new elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-3-1. (2) If cracks are found that do not extend inboard from station 41.0, outboard of station 45.0, or into the spar caps, prior to further flight, accomplish the following: (i) Stop drill any cracks found. (ii) Install Service Kit No. 12 by accomplishing paragraphs B-5 through B-20 of the MODIFICATION INSTRUCTIONS in the instructions for GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 1991. (iii) Balance the elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-1-1. (iv) Reinstall the elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-3-1. (3) If no cracks are found, prior to further flight, accomplish the following: (i) Install Service Kit No. 12 by accomplishing paragraphs B-5 through B-20 of the MODIFICATION INSTRUCTIONS in the instructions for GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 1991. (ii) Balance the elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-1-1. (iii) Reinstall the elevator in accordance with Gulfstream American Model GA-7 Maintenance Manual, Chapter 27-3-1. (b) 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.(c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. (d) The inspection and installation required by this AD shall be done in accordance with the instructions contained in GA-7/Cougar Aircraft Service Kit No. 12, referenced by American General Service Bulletin ME-1A, dated February 21, 1991. 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 American General Aircraft Corporation, Route 1, AB 306, P.O. Box 5757, Greenville, Mississippi 38703. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC. (e) This amendment (39-8188) becomes effective on April 17, 1992.
2001-17-08: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 series airplanes, that requires performing a general visual inspection to detect chafing or damage of the parallel power feeder cables of the number 2 integrated drive generator (IDG); repairing any chafed cable and damaged structure; and repositioning the parallel power feeder cables of the number 2 IDG. This action is necessary to prevent chafing and arcing of the parallel feeder cables of the number 2 IDG, which could result in smoke and/or fire in the right aft galley area. This action is intended to address the identified unsafe condition.
81-13-12 R1: 81-13-12 R1 DETROIT DIESEL ALLISON: Amendment 39-4179 as amended by Amendment 39-4701. Applies to all Model 250-C30, -C30P, and C30S engines and turbine assemblies equipped with 4th stage turbine nozzle assembly P/N 6898694 installed in aircraft certificated in all categories, EXCEPT: 1. Models 250-C30, -C30S: ENGINE SERIAL NO. TURBINE SERIAL NO. CAE 890690, 890691, CAT 95105, 95106, 890692, 890696, and subsequent 95108, 95109, and subsequent 2. Model 250-C30P: ENGINE SERIAL NO. TURBINE SERIAL NO. CAE 895086, 895087, and subsequent CAT 95110, 95111, 95112, and subsequent Compliance is required as indicated unless already accomplished. To prevent cracks in P/N 6898694 4th stage turbine wheel nozzles leading to uncontained turbine wheel failures accomplish the following: a. Inspect, reduce life limits where applicable based on inspection results, and remove from service affected P/N 6898694 nozzles in compliance with the schedule, instructions, and inspection criteria provided in Detroit Diesel Allison Commercial Engine Alert Bulletin CEB-A-72-3056, Revision 3 dated March 30, 1983, or later FAA approved revisions. b. Special flight permits may be issued in accordance with FAR's 21.197 and 21.199 to operate aircraft to a base where compliance with this AD can be accomplished. c. Upon request of the operator, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Chicago Aircraft Certification Office, FAA, 2300 East Devon Avenue, Des Plaines, Illinois 60018. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Detroit Diesel Allison, Division of General Motors Corporation, Indianapolis, Indiana 46206. These documents also maybe examined at the Office of Regional Counsel, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803 weekdays, except federal holidays, between 8:00 a.m. and 4:30 p.m. Amendment 39-4179 became effective August 10, 1981. This Amendment 39-4701 becomes effective September 26, 1983.
91-05-10: 91-05-10 FOKKER: Amendment 39-6905. Docket No. 90-NM-233-AD. Applicability: Model F-28 Mark 1000, 2000, 3000, and 4000 series airplanes, as listed in Part II of Fokker Report No. SE-243, Issue No. 1, dated June 1, 1990, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the airplane, accomplish the following: A. Accomplish the structural modifications according to the service bulletins and the "incorporation threshold" listed in Part II of Fokker Report No. SE-243, Issue No. 1, dated June 1, 1990 as follows: 1. For airplanes that have accumulated time-in-service exceeding the specified "incorporation threshold" as of the effective date of this AD, the structural modifications must be accomplished by the following dates: a. July 1, 1996, for those service bulletins to which [Note 1] applies. b. July 1, 1993, for those service bulletins to which [Note 2] applies. c. July 1, 1993, or 14 years after the airplane's manufacturing date, whichever occurs later, for service bulletins to which [Note 4] applies. 2. For airplanes that have accumulated time-in-service less than the specified "incorporation threshold" as of the effective date of this AD, the structural modifications must be accomplished before the applicable "incorporation threshold" or by the following dates, whichever occurs later: a. July 1, 1996, for service bulletins to which [Note 1] applies. b. July 1, 1993, for service bulletins to which [Note 2] applies. c. July 1, 1993, or 14 years after the airplane's manufacturing date, whichever comes later, for service bulletins to which [Note 4] applies. B. 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. 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. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6905, AD 91-05-10) becomes effective on March 25, 1991.