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79-06-06 R2: 79-06-06 R2 AVCO LYCOMING DIVISION: Amendment 39-3440 as amended by Amendment 39-3506 is further amended by Amendment 39-3795. Applies to all LTS101-600A, -600B, -600A-2, and -650A-2 turboshaft and LTP101-600 and -600A turboprop engines. Compliance required as indicated. 1. To prevent undetected lubrication system contamination leading to oil starvation of engine bearings and subsequent engine stoppage, accomplish the following within the next 5 hours of engine operation unless already accomplished and every 25 hours thereafter: Perform a spectrometric oil analysis as outlined in the applicable Avco Lycoming Engine Maintenance Manual, Chapter 71-00-00, and in accordance with Avco Lycoming Alert Notice, Reference 3V- W714, dated February 16, 1979, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. If any of the following spectrometric oil analysis limits are exceeded, inspect and repair, prior to further flight, in accordance with Chapter 72-00-00, Paragraph 13, of the appropriate Avco Lycoming Engine Maintenance Manual: a. Iron content, six parts per million. b. Between consecutive spectrometric oil analysis, iron content increases by three parts per million. c. Any other metal, five parts per million. NOTE: Engine operation not to exceed 4 calendar days or 25 hours between extraction of oil sample and obtaining spectrometric oil analysis results is authorized. 2. For LTP101-600 and 600A turboprop engines, S/N LE 50001 through S/N LE 50017, the requirements of paragraph 1 may be discontinued after the power turbine rotor assembly P/N 4-143-010-01/-02 is replaced with either: a. Rotor assembly P/N 4-143-010-01/02 with "APOLS93277" etched on rear face of wrenching surface, or b. Rotor assembly P/N 4-143-010-03, in accordance with Avco Lycoming Service Bulletin No. LTP101-72-0003, Revision 1, dated May 21, 1979, or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 3. For LTS101-600A, -600B, -600A-2, and -650A-2 turboshaft engines, the requirements of Paragraph 1 may be discontinued if the engine installation incorporates a full flow scavenge chip detector, TEDECO P/N A615 or equivalent, installed in accordance with STC SH2929SW or equivalent method approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region. 4. For all engines affected by this AD, the requirements of Paragraph 1 may be discontinued if the equivalent means of detecting lubrication system contamination, approved by the Chief, Engineering and Manufacturing Branch, FAA, New England Region, are effected. Avco Lycoming Alert Notice, Reference 3V-W714, dated February 16, 1979, and Service Bulletin No. LTP101-72-0003, Revision 1, dated May 21, 1979, refer to this subject. The manufacturer's Alert Notice, Service Bulletin, and Manuals identified and described in this directive are incorporated herein and madea 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 Director, Customer Service, Avco Lycoming Division, 550 South Main Street, Stratford, Connecticut 06514. These documents may also be examined at Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, and FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. 20591. Amendment 39-3440 became effective upon publication in the FEDERAL REGISTER except for recipients of the Emergency AD, dated February 23, 1979, for whom it became effective upon receipt. Amendment 39-3506 became effective upon publication in the FEDERAL REGISTER. This Amendment 39-3795 becomes effective June 2, 1980.
2000-05-24: This amendment adopts a new airworthiness directive (AD) that applies to all aircraft equipped with a certain Honeywell International Inc. (Honeywell) KAP 140 or KFC 225 autopilot system. AlliedSignal Avionics Inc. manufactured these autopilot systems before transferring the design data to Honeywell. This AD requires that you inspect the autopilot servo actuator for a loose fastener and modify the autopilot servo actuator when a loose fastener is found. This AD is the result of a report of failure of the autopilot servo actuator to disengage when the autopilot power was removed. The actions specified by this AD are intended to detect and correct a loose fastener in the autopilot servo actuator, which could cause the autopilot servo actuator to not disengage when power to the autopilot is removed. This could cause the pilot to experience additional control forces.
53-11-02: 53-11-02 de HAVILLAND: Applies to Model DHC-2 (Beaver) Aircraft, Serial Numbers 1 to 445 Inclusive. Compliance required as indicated. Cases have been reported of chafing of the engine oil sump by section assemblies. (P/N C2-E-105ND) and (P/N C2-E-107ND) of accessory firewall. An enlarged flange clearance is required to be incorporated as soon as possible but not later than the next 100 hours. The FAA concurs in this mandatory action by the Canadian Department of Transport. (de Havilland Technical News Sheet, Series B, No. 64 dated March 23, 1953, available from de Havilland Aircraft of Canada, Ltd., Toronto, Ontario, Canada, covers this same subject and describes method of repair.)
90-25-16: 90-25-16 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 6827. Docket No. 90-NM-147-AD. Applicability: All de Havilland Model DHC-7 series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent possible malfunction of the right main landing gear (MLG), accomplish the following: A. Within 100 landings after May 29, 1990 (the effective date of AD 90-09-02), and thereafter at intervals not to exceed 500 landings, conduct a visual inspection of the right MLG frame and attachment bolts, in accordance with paragraph A. of the Accomplishment Instructions in de Havilland Service Bulletin No. 7-24-66, Revision B, dated June 23, 1989. 1. If no damage is found, reassemble parts and return the airplane to service. 2. If damage is found, replace with serviceable parts prior to further flight, in accordance with the service bulletin. B. Within 180 days after the effective date ofthis AD, install Modification No. 7/2577, which relocates the external power grounding stud, in accordance with paragraph B of the Accomplishment Instructions in de Havilland Service Bulletin No. 7-24-66, Revision B, dated June 23, 1989. Installation of this modification constitutes terminating action for the repetitive inspections required by paragraph A., above. 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, New York Aircraft Certification Office (ACO), ANE-170. NOTE: The request should be submitted directly to the Manager, New York Aircraft ACO, ANE-170, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, New York ACO, ANE-170. 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 Boeing of Canada, Ltd., de Havilland Division, Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York. Airworthiness Directive 90-25-16 supersedes AD 90-09-02, Amendment 39-6579. This amendment (39-6827, AD 90-25-16) becomes effective on January 14, 1991.
91-18-13: 91-18-13 SHORT BROTHERS, PLC: Amendment 39-8015. Docket No. 91-NM-92-AD. Supersedes AD 91-04-06. Applicability: Model SD3-30 series airplanes, as listed in Short Brothers Service Bulletin SD330-24-25, Revision 2, dated November 29, 1990; and Model SD3-60 series airplanes, as listed in Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of power to the pitot/static heaters and subsequent incorrect airspeed and altitude information being provided to the pilot and/or co-pilot in the event of a generator or engine failure, accomplish the following: A. For Model SD3-30 series airplanes, Serial Numbers SH3002 through SH3072: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with Part A of the Accomplishment Instructions in Short Brothers Service Bulletin SD330-24-25, Revision 2, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Procedures Sections of the FAA-approved Airplane Flight Manual (AFM) by inserting AFM Amendment Document No. SBH 3.3 (ref. change P/15) or SBH 3.6 (ref. change P/11), as applicable. B. For Model SD3-30 series airplanes, Serial Numbers SH3073 and subsequent: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with Part B of the Accomplishment Instructions in Short Brothers Service Bulletin SD330-24-25, Revision 2, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Procedures Sections of the FAA-approved AFM by inserting AFM Amendment Document No. SBH 3.3 (ref. change P/15) or SBH 3.6 (ref. change P/11), as applicable. C. For Model SD3-60 series airplanes, Serial Numbers SH3601 through SH3619: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with the Part A of the Accomplishment Instructions in Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Sections of the FAA-approved AFM by inserting AFM Amendment Document No. SB 4.3 (ref. change P/18), SB 4.6 (ref. change P/11), or SB 4.8 (ref. change P/8), as applicable. D. For Model SD3-60 series airplanes, Serial Numbers SH3620 through SH3676: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with the Part B of the Accomplishment Instructions in Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Procedures Sections of the FAA-approved AFM by inserting AFM Amendment Document No. SB 4.3 (ref. change P/18),SB 4.6 (ref. change P/11), or SB 4.8 (ref. change P/8), as applicable. E. For Model SD3-60 series airplanes, Serial Numbers SH3677 through SH3762: Within 180 days after the effective date of this AD, revise the power source for the pitot/static heaters, in accordance with the Part C of the Accomplishment Instructions in Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990. Following accomplishment of this modification, revise the Emergency and Normal Procedures Sections of the FAA-approved AFM by inserting AFM Amendment Document No. SB 4.3 (ref. change P/18), SB 4.6 (ref. change P/11), or SB 4.8 (ref. change P/8), as applicable. F. 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. G. 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. H. The modification requirement shall be done in accordance with Short Brothers Service Bulletin SD330-24-25, Revision 2, dated November 29, 1990, and Short Brothers Service Bulletin SD360-24-18, Revision 3, dated November 29, 1990. The revisions to the Airplane Flight Manual (AFM) shall be done in accordance with the following list of AFM Amendment Documents and related effective pages: AFM Amendment Document Number Page Number Section Number SBH 3.3 17 37 3 4 SBH.3.6 17 43 3 4 SB.4.3 15 43 3 4 SB.4.6 15 43 3 4 SB.4.8 15 43 3 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 Short Brothers, PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3719. 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. Airworthiness Directive 91-18-13 supersedes AD 91-04-06 Amendment 39-6897. This amendment (39-8015, AD 91-18-13) becomes effective on October 16, 1991.
89-03-14: 89-03-14 AIRBUS INDUSTRIE: Amendment 39-6125. Applicability: Model A300-600 series airplanes, as listed in Airbus Industrie Service Bulletin A300-53-6024, Revision 1, dated July 8, 1988. Compliance: Required as indicated, unless previously accomplished. To prevent separation of the rear passenger/crew door from the airplane and subsequent rapid decompression, accomplish the following: A. Prior to the accumulation of 8,000 landings or within the next 1,000 landings after the effective date of this AD, whichever occurs later, inspect frame 73A RH and LH between beams 5 and 7 in accordance with Airbus Industrie Service Bulletin A300-53-6024, Revision 1, dated July 8, 1988. 1. If cracks are detected that are less than 0.4 inch, modify the frame within the next 2,500 landings, in accordance with Airbus Industrie Service Bulletin A300-53-6019, Revision 3, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 1,250 landings until the modification is accomplished. 2. If cracks are detected that are equal to or more than 0.4 inch but less than 0.8 inch, modify the frame within the next 1,500 landings, in accordance with Airbus Industrie Service Bulletin A300-53-6019, Revision 3, dated October 13, 1988. The inspection must be repeated at intervals not to exceed 750 landings until the modification is accomplished. 3. If cracks are detected that are equal to or more than 0.8 inch, prior to further flight, modify the frame in accordance with Airbus Industrie Service Bulletin A300-53- 6019, Revision 3, dated October 13, 1988. 4. If no cracks are detected, repeat the inspection at intervals not to exceed 4,000 landings. B. The repetitive inspections required by paragraph A., above, may be terminated following completion of the modification of the door frame structure in accordance with Airbus Service Bulletin A300-53-6019, Revision 3, dated October 13, 1988. 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, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments 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 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 documents from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6125, AD 89-03-14) becomes effective March 7, 1989.
2000-06-02: This document adopts a new airworthiness directive (AD) that applies to all Dornier Luftfahrt GmbH (Dornier) 228 series airplanes that are equipped with pneumatic deicing boots. This AD requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
2000-05-27: This amendment supersedes an existing airworthiness directive (AD), applicable to certain British Aerospace Model BAe 146-100A, -200A, and -300A series airplanes, that currently requires either a one-time nondestructive test (NDT) inspection or a detailed visual inspection for cracking of the fuselage skin in the vicinity of frame 29 between stringers 12 and 13, and repair, if necessary. This amendment requires that the current thresholds for these inspections be reduced and that repetitive inspections be performed. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct fatigue cracking of the fuselage skin in the specified area, which could result in reduced structural integrity of the airplane.
2000-05-19: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 727 series airplanes, that requires a one-time detailed visual inspection of the fuselage skin and bonded doubler area above the forward entry doorway to detect fatigue cracking or the existence of certain repairs, and follow-on corrective actions, if necessary. This action also requires a preventive modification or full-sized repair doubler, as applicable. This amendment is prompted by reports of fatigue cracking in the fuselage skin and bonded doublers in the forward and aft corners above the forward entry doorway. The actions specified by this AD are intended to prevent such fatigue cracking of the fuselage skin and bonded doubler, which could result in reduced structural integrity and consequent loss of cabin pressurization.
2000-06-03: This document adopts a new airworthiness directive (AD) that applies to all Bombardier Inc. (Bombardier) Models DHC-6-1, DHC-6-100, DHC-6-200, and DHC-6-300 airplanes that are equipped with pneumatic deicing boots. This AD requires revising the Airplane Flight Manual (AFM) to include requirements for activation of the airframe pneumatic deicing boots. This AD is the result of reports of in-flight incidents and an accident that occurred in icing conditions where the airframe pneumatic deicing boots were not activated. The actions specified by this AD are intended to assure that flightcrews activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation. This action will prevent reduced controllability of the aircraft due to adverse aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.