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91-11-12: 91-11-12 BRITISH AEROSPACE: Amendment 39-7010. Docket No. 91-NM-16-AD. Applicability: All Viscount Model 810 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent in-flight separation of an entrance or emergency door from the airplane and subsequent decompression of the passenger cabin, accomplish the following: A. Within 90 days after the effective date of this AD, perform a non-destructive testing (NDT) X-ray inspection of the forward passenger door, and of the rear entrance and rear emergency doors, for incorrectly machined door operating torque shaft coupling sleeves, in accordance with Viscount Preliminary Technical Leaflet (PTL) No. 194, Revision 1, dated December 1989. B. If incorrectly machined door operating torque shaft coupling sleeves are found, prior to further flight, replace the sleeves with correctly machined serviceable parts in accordance with Viscount PTL No. 194, Revision 1, dated December 1989. C. 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, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, 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 (39-7010, AD 91-11-12) becomes effective on July 1, 1991.
92-27-15: 92-27-15 DE HAVILLAND, INC.: Amendment 39-8450. Docket No. 92-NM-137-AD. Applicability: All Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent freezing of the elevator servo drum assembly, which could lead to an uncommanded pitch excursion with the autopilot engaged and reduced controllability of the aircraft, accomplish the following: (a) Within 60 days after the effective date of this AD, install a water deflector onto the front spar of the vertical stabilizer, directly over the elevator servo assembly, Modification No. 7/2605, in accordance with paragraph III. of de Havilland Service Bulletin S.B. 7-55-10, dated October 25, 1991. (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, 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. (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 de Havilland Service Bulletin S.B. 7-55-10, dated October 25, 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 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 11581; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on February 8, 1993.
99-11-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Mooney Aircraft Corporation (Mooney) Model M20R airplanes. This AD requires either fabricating and installing a placard that specifies using the air conditioning system during cruise operations only or deactivating the air conditioning system so it cannot be used. This AD is the result of reports of the existence of dangerous levels of carbon monoxide during taxi, climb, and descent operations of the above-referenced airplanes. The actions specified by this AD are intended to prevent dangerous levels of carbon monoxide from entering the airplane cabin during takeoff, climb, and descent operations caused by the present flight cabin sealing design of the affected airplanes, which could result in passenger injury.
68-16-04: 68-16-04 GENERAL DYNAMICS: Amendment 39-638. AD 68-16-04 is revised as indicated. Applies to General Dynamics Model 240 airplanes equipped with Rolls Royce MK 542-4 engines and Dowty Rotol (c)R245/4-40-4.5/13 propellers in accordance with General Dynamics Supplemental Type Certificate SA1054WE (hereinafter referred to as the CV-600) and General Dynamics Model 340 and 440 airplanes equipped with Rolls Royce MK 542-4 engines and Dowty Rotol (c) R245-4-40-4.5/13 or Dowty Rotol (c)R259/4-40-4.5/17 propellers in accordance with General Dynamics Supplemental Type Certificate SA1096WE (hereinafter referred to as the CV-640). Compliance required as indicated unless already accomplished. To eliminate potential flammable fluid ignition sources in the main landing gear wheel well accomplish the following unless already accomplished: (A) Inspection requirements, CV-600 and CV-640 (1) Compliance required within the next 50 hours' time in service after the effective date of this Airworthiness Directive unless already accomplished within the last 135 hours' time in service and thereafter not to exceed 185 hours' time in service. (a) Inspect the mating surfaces of the engine exhaust duct flange joint thermal insulation collar, P/N's 2D6220119-31, -41, and -43 with the engine exhaust duct thermal insulation blanket assemblies for possible gaps. For purposes of this inspection, the engine exhaust system component temperatures shall be no greater than the outside ambient air temperature. (b) If gaps are found, the thermal insulation collar and/or adjacent thermal insulation blanket must be replaced with new or overhauled insulation collars and/or blankets. (2) Compliance required within the next 125 hours' time in service after the effective date of this Airworthiness Directive unless already accomplished within the last 125 hours' time in service and thereafter not to exceed 250 hours' time in service. (a) Inspect the engine exhaust duct flange joints for leakage by inspection of the gaskets and the internal surface of the thermal insulation collars, Part Numbers 2D6220119-31, -41, and -43, or by an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) If exhaust leakage is found, replace exhaust duct flange joint gaskets with two gaskets, General Dynamics/Convair P/N 2D6220115-15, at the forward flange and two gaskets, General Dynamics/Convair P/N 2D6220127-9, at the aft flange or equivalent replacements approved by the Chief, Aircraft Engineering Division, FAA, Western Region. (3) Upon request of the operator, FAA Maintenance Inspectors, subject to prior approval of the Chief, Aircraft Engineering Division, FAA Western Region, may adjust the repetitive inspection intervals specified in this Airworthiness Directive to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. (4) Upon completion of the work described in (B)(1)(a), below, the inspection requirement of (A) is no longer applicable. (B) Modification and Relocation Requirements, CV-600 and CV-640 (1) Within the next 4,000 hours' time in service after the effective date of this Airworthiness Directive unless already accomplished. (a) Modify the engine exhaust duct flange joint thermal insulation collars, P/N's 2D6220119-31, -41 and -43 in accordance with General Dynamics Service Bulletin 600(240D) 640(340D) S.B. No. 78-3 or later FAA approved revision or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (b) Modify the electrical insulation in the alternating current generator control unit (P/N 914F597) in accordance with Westinghouse Aerospace Service Bulletins 67-802 and 67-803 or later FAA approved revisions or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region.(c) Relocate the alternating current generator control unit (P/N 914F597) as follows: (i) For CV-600 aircraft, per General Dynamics Service Bulletin 600(240D) S.B. No. 24-1 or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region; and (ii) For CV-640 aircraft per General Dynamics Service Bulletin 640(340D) S.B. No. 24-2 or later FAA approved revision or an equivalent method approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective on December 27, 1968.
86-15-06: 86-15-06 AVIONS MARCEL DASSAULT - BREGUET AVIATION: Amendment 39-5363. Applies to AMD Falcon 10 series airplanes, serial numbers 1 thru 196 inclusive, and 198 thru 201 inclusive, certificated in any category. Compliance is required within 60 days after the effective date of this AD. To ensure the proper installation of the rudder servo actuator hydraulic lines, accomplish the following, unless already accomplished: A. Modify the rudder servo actuator system in accordance with AMD-BA Service Bulletin F10-27-028 (0237), dated June 24, 1983. 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, Northwest Mountain Region. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of inspections and/or modifications required by this AD. All persons affected by this directive, who have not already received the appropriate service bulletin from the manufacturer, may obtain copies upon request to the AMD-BA Representative, c/o F.J.C., Teterboro Airport, Teterboro, New Jersey 07608. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5363, becomes effective August 25, 1986.
87-18-06 R1: 87-18-06 R1 BEECH: Amendment 39-5721 as amended by amendment 39-5837 applies to model and serial numbered airplanes listed below equipped with the optional hydrolock seat recline actuators on co-pilot and third and fourth seats, certificated in any category: MODEL SERIAL NUMBERS F33A CE-919, CE-923, CE-925, CE-927, CE-929, thru CE-1083 V35B D-10348, D-10353 thru D-10403 A36 E-1422, E-1551, E-1569, E-1581, E-1594 thru E-2327 A36TC and B36TC EA-21, EA-28, EA-33 thru EA-454 E55 TE-1152, TE-1181 thru TE-1201 58 and 58A TH-1027, TH-1062, TH-1067, TH-1080 thru TH-1507 58P and 58PA TJ-210, TJ-235 thru TJ-497 58TC and 58TCA TK-107, TK-108, TK-110 thru TK-151 Compliance: Required within the next 100 hours time-in-service or the next scheduled inspection, whichever occurs first after the effective date of this revised AD, unless already accomplished per the original issuance of this AD. To prevent the co-pilot and/or passenger chair armrest from coming in contact with the seat recline actuator handle and inadvertently releasing the locking feature on the seatback, accomplish the following: (a) Replace the seat recline actuator handle on the co-pilot's and the third and fourth passenger seats that are equipped with reclining backs, with a new P/N 102-530111-5 handle assembly in accordance with the instructions in Beech Service Bulletin No. 2175, revision dated June 1987. NOTE: The third and fourth passenger seats are the seats immediately behind the pilot's and co-pilot's seats. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Beech Aircraft Corporation, Commercial Service, Dept. 52, P.O. Box 85, Wichita, Kansas 67201-0085, or may examine these documents at the FAA, Office of the Regional Counsel, 601 East 12th Street, Room 1558, Kansas City, Missouri 64106. This amendment 39-5837 revises AD 87-18-06, Amendment 39-5721, effective October 9, 1987. This amendment 39-5837 becomes effective on February 5, 1988.
2013-21-08: We are adopting a new airworthiness directive (AD) for certain ATR--GIE Avions de Transport R[eacute]gional Model ATR72-101, -201, - 102, -202, -211, -212, and -212A airplanes. This AD was prompted by reports of airplane incidents and accidents that have occurred because of low-level fuel tank situations and fuel starvation that resulted in engine flameouts. This AD requires installing a fuel quantity indicator (FQI) equipped with a locking adaptor on the electrical connector. We are issuing this AD to prevent an engine flame-out, which could result in reduced controllability of the airplane.
49-18-01: 49-18-01 CURTISS-WRIGHT Applies to all Models of C-46 Series airplanes used in passenger operation under provisions of Part 41, 42, or 61 of the Civil Air Regulations as specified in Sections 41.20 (f), 61.30 and Amendment 42-8. To be accomplished not later than the dates specified in above amendments as revised by Special Civil Air Regulation No. 329 and any subsequent regulations affecting these compliance dates. (This AD pertains only to combustion heater fire protection aspects of the above Regulation Amendments. Separate AD's will be issued covering fire protection for the powerplant installation and for the baggage and cargo compartments of the airplane). (1) Each heater exhaust pipe shall be completely enclosed with well-ventilated, fireproof shrouds. (2) Each heater combustion chamber shall be drained to the exterior of the airplane. All such drain lines shall be of fireproof construction and contain no traps in the normal flight or ground attitudes.(3) The heater fuel components presently mounted on top of each heater shall be located in fuel and fume proof enclosures, ventilated and drained to the exterior of the airplane. (4) The thermal overheat switches for each heater shall be rigged to shut off the fuel supply and ignition circuits of the heaters when overheating occurs. These switches must also be arranged so as to prevent their automatically recycling to "ON" once overheating has occurred. The present overheat switches are not intended to be used as cycling switches. In cycling to produce the required heat is necessary, it must be accomplished at a lower temperature by an additional cycling switch controlling a cycling solenoid. (5) A manual fuel shutoff valve shall be provided. (USAF Technical Order 01- 25LA-211 describes such an installation.) (6) Adequate fire extinguisher and fire detector installations shall be provided for each heater. The fire detector installation shall contain at least one detector centrally located over the heaters in the heater area and one detector in the ventilating air duct of each heater just aft of the combustion chamber. The fire extinguisher system should provide at least 1 pound of carbon dioxide for each heater directed into the inlet side of the ventilating air stream. Instructions for operating this carbon dioxide system should also require that the ventilating air duct valve be closed when carbon dioxide is injected to the heater. With the arrangement as described, no flight tests of carbon dioxide contamination of the pilots compartment or cabin area need be conducted. As outlined in the Airworthiness Directive concerning fire protection for the baggage and cargo compartments, however, flight tests to establish smoke evacuation procedures for the cargo compartments when these compartments are carrying cargo, will need to be accomplished. The results of these tests will determine the procedure to be followed to rid the airplane of noxious gases. (7) Revision pages for the Airplane Flight Manual must be prepared to cover emergency fire procedures as well as smoke and other noxious gas elimination procedures.
93-07-05: 93-07-05 AMI INDUSTRIES, INC.: Amendment 39-8537. Docket 92-NM-184-AD. Applicability: Pilot and Co-Pilot Seats, Model 1108, serial numbers 004 to 189, inclusive; as installed in, but not limited to de Havilland Model DHC-8 series airplanes. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the pilot's and co-pilot's lap belts during air turbulence, which could lead to reduced ability of the pilots to control the airplane, accomplish the following: (a) Within 60 days after the effective date of this AD, remove the lap belt attachment links and install the improved lap belt attachment link kit, P/N 1B9014-3R, in accordance with AMI Industries, Inc., Service Bulletin 25-1108-03, dated May 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, Seattle Aircraft Certification Office (ACO). Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Seattle ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Seattle ACO. (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 replacement shall be done in accordance with AMI Industries, Inc., Service Bulletin 25-1108-03, dated May 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 AMI Industries, Inc., 1275 North Newport Road, Colorado Springs, Colorado 80916. 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 May 10, 1993.
2022-14-03: The FAA is adopting a new airworthiness directive (AD) for all Leonardo S.p.a. Model AB412 and AB412 EP helicopters. This AD was prompted by reports of cracked tailboom attachment bolts and barrel nuts. This AD requires replacing the upper left hand (LH) tailboom attachment bolt, visually inspecting the other three tailboom attachment bolts and all barrel nuts, repetitive torque checks of the tailboom attachment bolts, and corrective action if necessary, 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.