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2001-13-09: This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2-1C, B2-203, B2K-3C, B4-2C, B4-103, and B4-203 series airplanes, that requires a one-time inspection of the space between the fuel quantity indication (FQI) probes and any adjacent structures for minimum clearance, and corrective action, if necessary. The actions specified by this AD are intended to prevent the possibility of electrical arcing to the fuel tank if the airplane should be struck by lightning. This action is intended to address the identified unsafe condition.
90-26-07: 90-26-07 BRITISH AEROSPACE: Amendment 39-6834. Docket No. 90-NM-172-AD. Applicability: All Model BAC 1-11 200 and 400 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the glazing frame and possible rapid decompression of the airplane, accomplish the following: A. For airplanes operating at a maximum cabin differential pressure of 7.5 pounds per square inch (psi): Prior to the accumulation of 20,000 landings on the glazing frame since new, or within 1,600 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,600 landings, perform an internal and external visual inspection, or non-destructive testing (NDT) inspection, of the pilot's and co-pilot's direct view (DV) window aperture (flight deck side glazing frame at Pillars B and C), in accordance with the Accomplishment Instructions of BritishAerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March 21, 1990. B. For airplanes modified for operation above 7.5 psi to a maximum of 8.2 psi cabin differential pressure: Prior to the accumulation of 14,000 landings on the glazing frame since new, or within 1,100 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 1,100 landings, perform an internal and external visual inspection, or non-destructive testing (NDT) inspection, of the pilot's and co-pilot's DV window aperture (flight deck side glazing frame at Pillars B and C), in accordance with the Accomplishment Instructions of British Aerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March 21, 1990. C. If cracks are found during the inspections required by paragraph A. and B. of this AD, prior to further flight, perform an eddy current inspection, in accordance with British Aerospace Alert Service Bulletin 53-A-PM5985, Issue 1, dated March21, 1990; and 1. For cracks equal to or less than 0.2 inch, damage may be blended out in accordance with Table 1 or Table 2 of the service bulletin, as appropriate. 2. All other cracks must be repaired in accordance with the Structural Repair Manual, as specified in Table 1 and Table 2 of the service bulletin, as appropriate; or repaired in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate; or the glazing frame must be replaced with a serviceable part. 3. If blending has been previously accomplished, all cracks must be repaired in accordance with the BAC 1-11 Structural Repair Manual, as specified in Table 1 or Table 2 of the service bulletin, as appropriate; or repaired in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. 4. Following repair or replacement, the inspections specified in paragraphs A. and B. of this AD are still required. D. 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. E. 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 British Aerospace, PLC, Librarian for Service Bulletins, Dulles International Airport, P.O. Box 17414, Washington, D.C. 20041-0414. These documents may be examined at the FAA,Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6834, AD 90-26-07) becomes effective on January 16, 1991.
93-23-04: 93-23-04 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE AND EUROCOPTER FRANCE: Amendment 39-8738. Docket Number 93-SW-02-AD. Applicability: Model SE 3160, SA 315B, SA 316B, SA 316C, and SA 319B series helicopters equipped with main rotor blades, part number (P/N) LOM3160-100 installed in accordance with Supplemental Type Certificate (STC) No. SH778GL, certificated in any category. Compliance: Required within 25 hours' time-in-service after the effective date of this airworthiness directive (AD), unless accomplished previously. To prevent excessive main rotor vibrations that could result in failure of rotor system components, and subsequent loss of control of the helicopter, accomplish the following: (a) Install an outside air temperature (OAT) and velocity never exceed (VNE) airspeed limitation flip chart placard, P/N LOM3160-151, on top of the instrument panel immediately to the right of the existing VNE placard, using velcro strips as described in Les "Blades"De L'Helicoptere, Ltd. Service Information Letter No. 1-11-92A, dated December 3, 1992. (b) After compliance with paragraph (a) of this AD, operate the helicopter in accordance with the Helicopter Flight Manual Supplement, approved and dated November 25, 1992, that is applicable to helicopters modified in accordance with STC SH778GL. (c) An alternate method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3229 East Spring Street, Long Beach, California 90806-2425. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Los Angeles Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Manager, Los Angeles Aircraft Certification Office. (d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the helicopter to a location where the requirements of this AD can be accomplished, provided the indicated airspeed is limited to no more than 50 knots. (e) The installation shall be done in accordance with Les "Blades" de l'Helicoptere, Ltd. Service Information Letter No. 1-11-92A, dated December 3, 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 Les "Blades" de l'Helicoptere, Ltd., 5132 Greencrest Road, La Canada Flintridge, California 91011. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 4400 Blue Mound Road, bldg. 3B, room 158, Fort Worth, Texas 76106; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective February 17, 1994.
77-15-07: 77-15-07 BRITISH AIRCRAFT CORPORATION: Amendment 39-2980. Applies to Viscount Model 744, 745D, and 810 airplanes with aileron control rods, P/N 60903, sheets 185 and 187 and P/N 70103, sheets 329, 445, 447, 449, 451, 453, 455, 457, and 459, certificated in all categories. Compliance is required as indicated, unless already accomplished. To detect corrosion of the aileron control rods and prevent possible aileron failure, accomplish the following: (a) Within the next 30 days after the effective date of this AD or 18 months from the date of the last overhaul of the specified aileron control rods, whichever occurs later, and thereafter at intervals not to exceed 6 months from the last inspection, inspect the aileron control rods for corrosion in accordance with paragraph 2.2 "Accomplishment Instructions" section of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and NO. 174 for 810 series airplanes, or an FAA-approved equivalent. (b) If, during an inspection required by paragraph (a) of this AD, corrosion is found, before further flight, replace the corroded parts with new parts of the same part number. (c) If, during an inspection required by paragraph (a) of this AD, no corrosion is found, rework the aileron control rods in accordance with paragraph 2.2.1 "Accomplishment Instructions" section of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and No. 174 for 810 series airplanes, or an FAA-approved equivalent. (d) The repetitive inspections required by paragraph (a) of this AD may be discontinued upon compliance with paragraph (e) of this AD. (e) Within the next 2 years after the effective date of this AD or at the next aileron control rod overhaul, whichever occurs sooner, remove the affected aileron control rods, disassemble the external sleeves where fitted, and conducta radiographic inspection of the aileron control rod tubes and a visual inspection of the external sleeves in accordance with paragraph 2.4 "Accomplishment Instructions" and paragraph entitled "Radiographic Technique" of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and NO. 174 for 810 series airplanes, or an FAA-approved equivalent. (f) If, during the inspection required by paragraph (e) of this AD, corrosion is found, before further flight, replace the corroded parts with new parts of the same part number. (g) If, during the inspection required by paragraph (e) of this AD, no corrosion is found, rework the aileron control rods in accordance with paragraph 2.4 "Accomplishment Instructions" section of issue 2, dated June 2, 1976, British Aircraft Corporation Alert Preliminary Technical Leaflets No. 305 for 700 series airplanes and No. 174 for 810 series airplanes, or an FAA-approved equivalent.This amendment becomes effective August 22, 1977.
2016-20-01: We are adopting a new airworthiness directive (AD) for Bell Model 427 and Model 429 helicopters. This AD requires replacing certain engine and transmission oil check valves. This AD also prohibits installing the affected check valves on any helicopter. This AD is prompted by a report of several cracked or leaking check valves. These actions are intended to detect and prevent a cracked or leaking check valve which could result in loss of lubrication to the engine or transmission, failure of the engine or transmission, and subsequent loss of control of the helicopter.
2001-12-51: This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-12-51 that was sent previously to all known U.S. owners and operators of all Boeing Model 737-800 series airplanes by individual notices. This AD requires revising the Airplane Flight Manual (AFM) to prohibit operating the airplane at speeds in excess of 300 knots indicated airspeed (KIAS) with speedbrakes extended. This AD also provides for optional terminating action for the AFM revision. This action is prompted by a report indicating that severe vibration of the horizontal stabilizer occurred on a Boeing Model 737-800 series airplane. The actions specified by this AD are intended to prevent severe vibration of the elevator and elevator tab assembly following deployment of the speedbrakes, which, if not corrected, could result in severe damage to the horizontal stabilizer, followed by loss of controllability of the airplane.
90-13-01 R1: 90-13-01 R1 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-8034. Docket No. 90-ASW-35. Final rule of priority letter AD. Applicability: Model 206B, 206L, 206L-1, and 206L-3 helicopters, all serial numbers, certificated in any category. Compliance: Required before further flight, unless already accomplished. To prevent failure of a tail rotor blade assembly, which could result in loss of control of the tail rotor, accomplish the following: (a) Determine the part number and serial number of the tail rotor blade assembly installed on the helicopter. (b) If the tail rotor blade assembly installed is P/N 206-016-201-113 or P/N 206- 016-201-127 and is identified with any serial number listed below, remove and replace the blade assembly with an airworthy part before further flight: T-41361 T-41627 T-41725 T-41737 T-42088 T-42127 T-42157 T-42307 T-42311 T-42316 T-42494 T-42496 T-42497 T-42502 T-42523 T-42534 T-43276 T-44089 T-44120 T-44157 T-44174 Serial Numbers: T-44222 T-44300 T-44638 (c) If one of the tail rotor blade assemblies listed in paragraph (b) is found, report the helicopter registration, serial number, and tail rotor blade assembly serial number to the Manager, Rotorcraft Certification Office, ASW-170, Federal Aviation Administration, Fort Worth, Texas, 76193-0170, telephone (817) 624-5170, within 10 days of the inspection. (Reporting approved by the Office of Management and Budget under OMB No. 2120-0056.) (d) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the tail rotor blade assembly replacement may be accomplished. NOTE: Any unairworthy blade assemblies found as a result of (b) of this AD should be permanently marked as unairworthy. (e) Record compliance with paragraph (b) of this AD in the AD compliance record and in the maintenance record of the helicopter log book. This record must include the serial numbers of any deficient blade assembly found during compliance with this AD. (f) An alternate method of compliance which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170. This amendment (39-8034, AD 90-13-01 R1) becomes effective on October 17, 1991, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD's 90-13-01 and 90-13-01 R1, issued June 14 and June 22, 1990, which contained this amendment.
2016-19-11: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by a malfunctioning No. 2 engine intake heater with corrosion on the thermostats and the fuselage skin where the thermostats made contact with the aircraft fuselage skin. This AD requires a general visual inspection for corrosion of the thermostats' mounting surfaces and fuselage skin surface, corrective actions if necessary, and relocating the existing thermostats. We are issuing this AD to prevent corrosion within the thermostats that might cause the switch mechanism to seize in the open position and prevent the activation of the associated engine air intake heater. An inactive engine air intake heater could lead to an engine failure.
78-26-01: 78-26-01 DETROIT DIESEL ALLISON: Amendment 39-3373. Applies to Model 250-C28B engines installed in but not limited to Bell Model 206L-1 rotorcraft certificated in all categories. Compliance required as indicated, unless previously accomplished. To preclude possible engine power loss resulting from electromagnetic interference, accomplish the following: (A) Before further flight accomplish the following unless the engine electrical system has been previously modified in accordance with Detroit Diesel Allison Commercial Engine Bulletin 73-2003. (1) Pull the N2 overspeed circuit breaker and secure by wrapping with tape or placing a Ty-Wrap around the breaker stem. (2) Install placard which states "Eng Ovsp Circuit Deactivated" in 1/4" or larger letters adjacent to N2 overspeed circuit breaker. Note: The engine overspeed test outlined in Section 2 of the RFM will no longer function with the circuit breaker deactivated. (B) Not later than February 1, 1979 modify the engine electrical system in accordance with Detroit Diesel Allison Commercial Engine Bulletin 73-2003 unless previously accomplished. Concurrent with the accomplishment of CEB 73-2003 reactivate the N2 overspeed control by engaging the N2 overspeed circuit breaker and removing the placard "Eng Ovsp Circuit Deactivated," and remove the No. 4 plug from the outlet vent of the N2 overspeed solenoid valve if installed in accordance with Detroit Diesel Allison Commercial Service Letter 2008. The Detroit Diesel Allison Commercial Engine Bulletin identified in this directive is incorporated herein and made part hereof pursuant to 5 U.S.C. 552(a)(1). The Detroit Diesel Allison Commercial Engine Bulletin incorporated herein may be obtained upon request to Detroit Diesel Allison, Division of General Motors Corporation, P.O. Box 894, Indianapolis, Indiana 46206. This document may also be examined at the FAA Great Lakes Region, 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 AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C. and the Great Lakes Region. (Detroit Diesel Allison Commercial Service Letter 250-C28B CSL-2008 also pertains to this subject.) This amendment becomes effective upon publication in the Federal Register, as to all persons except those persons to whom it was made immediately effective by the air mail letter dated November 3, 1978, which contained this amendment.
77-21-05: 77-21-05 ROLLS ROYCE AERO, LTD: Amendment 39-3055. Applies to Dart Engines Series 527, 528, 529, 531, 532, 533, 534, 535, 536, 550, 542-4, 542-10, and 543-10 that have modification 1425 incorporated and are installed on, but not necessarily limited to, Nihon YS-11, Convair 600 and 640, Handley Page Herald, Fokker F27, Fairchild F27, Grumman Gulfstream I, and Hawker Siddeley 748 series. Compliance is required as indicated. To prevent overheating and failure of high pressure turbine discs, accomplish the following: (a) Within the next 500 hours engine time in service after the effective date of this AD and thereafter at intervals not to exceed 1500 hours engine time in service, inspect the flame tube bridge pieces for cracking of the support legs in accordance with the instructions contained in paragraph 4.C of Rolls Royce Dart Service Bulletin Da 72-420, dated October 1975 (hereinafter referred to as the Bulletin), or an equivalent approved by the Chief, Aircraft Certification Staff, Europe, Africa, and Middle East Region, FAA, c/o American Embassy, APO New York, NY 09667 (hereinafter referred to as FAA-approved equivalent). (b) If, during an inspection required by this AD, flame tube bridge piece cracking is detected, replace the affected part with a serviceable part before further flight (except that the aircraft may be flown in accordance with FAR 21.197 and 21.199 to a base where the work can be performed), and continue to inspect in accordance with either paragraphs (c) or (d) of this AD, as applicable. (c) If, during an inspection required by paragraph (a) of this AD, flame tube bridge piece leg cracking is found, establish a repetitive inspection interval for all engines in the fleet in accordance with paragraph 4.A.(3)(b) of the Bulletin or an FAA-approved equivalent and continue to inspect the fleet in accordance with paragraph (a) of this AD within the fleet repetitive inspection interval established under this paragraph. (d) If, during a repetitive inspection conducted in accordance with this paragraph or paragraph (c) of this AD, a cracked bridge piece leg of any flame tube in the fleet is found, establish a further reduced repetitive inspection interval for all engines in the fleet in accordance with paragraph 4.B.(3) of the Bulletin or an FAA- approved equivalent and continue to inspect the fleet in accordance with paragraph (a) of this AD within the fleet repetitive inspection interval established under this paragraph. This amendment becomes effective November 11, 1977.