Aircraft-logs.com

Results
2010-20-18: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Investigation of a recent accident has indicated it is possible to exceed the aircraft aft C of G limits during parachute operations. It is the responsibility of the pilot in command to ensure that the aircraft is loaded within the approved weight and balance limitations and these limitations are not exceeded throughout the flight. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
66-13-05: 66-13-05 VERTOL: Amdt. 39-240 Part 39 Federal Register May 19, 1966. Applies to Model 107-II Helicopters. Compliance required within the next 130 hours' time in service after the effective date of this AD, unless already accomplished. To prevent further simultaneous engine false fire warnings caused by electrical wiring system malfunction: (a) Accomplish the following or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region (1) Isolate each fire detector system test circuit by replacing wafer test switch, P/N 1-1917- 1N5, with switch, P/N 1-1919-2N5; and (2) Revise the wiring arrangement in accordance with Vertol Service Bulletins Nos. 107-219 and 107-219A dated September 20, and October 22, 1965, respectively, or later FAA-approved revisions. (b) After modification in accordance with (a), functionally test the engine fire detection system as described in Vertol 107-2 Maintenance Manual, Chapter 16. Thisdirective effective June 18, 1966.
2010-20-05: The FAA is superseding an existing airworthiness directive (AD) for Turbom ca S.A. ARRIEL 2B turboshaft engines. That AD currently requires initial and repetitive inspections, cleaning, lubrication, and checks for proper operation of the hydro-mechanical unit (HMU) acceleration controller axle except on engines that incorporate modification TU 132. That AD also provides an optional terminating action for the repetitive inspections. This AD requires the same actions, but expands the applicability to include all engines that do not incorporate modification TU 149. This AD results from reports of engines with modification TU 132 incorporated experiencing stuck controller axles in the metering valve body. We are issuing this AD to prevent loss of control of engine fuel flow in manual control mode or mixed control mode, which can lead to engine overspeed, and in-flight engine shutdown resulting in a forced autorotation landing or accident.
2010-20-09: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Following five reported cases of balance washer screw failure on similar ADGs [air-driven generators]/ram air turbines installed on other aircraft types, investigation by Hamilton Sundstrand determined that a specific batch of the screws had a metallographic non-conformity that increased their susceptibility to brittle fracture. * * * Failure of a balance washer screw can result in loss of the related balance washer, with consequent turbine imbalance. Such imbalance could potentially result in ADG structural failure (including blade failure), loss of ADG electrical power and structural damage to the aircraft and, if deployment was activated by a dual engine shutdown, could also result in loss of hydraulic power for the flight controls. * * * * * The unsafe condition is the reduced ability of the flightcrew to maintain the safe flight and landing of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
88-20-03: 88-20-03 BRITISH AEROSPACE: Amendment 39-6029. Applies to certain British Aerospace (BAe) Model 146 series airplanes, as listed in BAe 146 Service Bulletin 53-70, Revision 1, dated July 15, 1988 (hereinafter referred to as SB 53-70), certificated in any category. Compliance required as indicated, unless previously accomplished. To detect cracking of the rear fuselage skin, accomplish the following: A. For Model BAe 146 200 and 200A series airplanes listed in paragraph 1.A.(1)(c) of SB 53-70: Prior to the accumulation of 18,000 landings, or within 30 days after the effective date of this AD, whichever occurs later and thereafter at intervals not to exceed 12,000 landings, inspect the lap joint at stringer 2 left, between fuselage stations 635.36 and 766.40, for cracks, in accordance with SB 53-70. If cracks are found which exceed the limits specified in SB 53-70, repair before further flight, in accordance with that service bulletin. B. For Model BAe 146 100, 100A, 200, and 200A series airplanes listed in paragraphs 1.A(1)(a), 1.A(1)(b), and 1.A(1)(c) of SB 53-70: Prior to the accumulation of 12,000 landings, or within 30 days after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 9,000 landings, inspect lap joints at stringer 10 left and right between fuselage stations 541.0 and 672.04 for the Model BAe 146 100 series, and 635.36 and 766.40 for the Model BAe 146 200 series, for cracks, in accordance with SB 53-70. If cracks are found which exceed the specified limits specified in SB 53-70, repair before further flight, in accordance with that service bulletin. NOTE: BAE 146 100 and 100A series airplanes that have previously complied with paragraph B. of AD 88-14-08, Amendment 39-5972, are considered to have complied with the initial inspection requirements of paragraph B. of this AD. The inspection is to be repeated in accordance with this AD at intervals not to exceed 9,000 landings, as indicated. C. For Model BAe 146 200 and 200A series airplanes listed in paragraph 1.A.(1)(c) of SB 53-70: Prior to the accumulation of 12,000 landings, or within 30 days after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 9,000 landings, inspect the lap joint at stringer 19 left, between fuselage stations 635.36 and 766.40, for cracks in accordance with SB 53-70. If cracks are found which exceed the limits specified in SB 53-70, repair before further flight, in accordance with that service bulletin. 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, 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.E. 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 the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment supersedes AD 88-14-08, Amendment 39-5972. This amendment, 39-6029, becomes effective October 13, 1988.
93-14-01: 93-14-01 JETSTREAM AIRCRAFT, LIMITED: Amendment 39-8625. Docket 93-NM-94-AD. Applicability: Model 4101 airplanes on which Modification JM41204 or Repair Scheme J41R0370 has not been installed, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent rapid loss of cabin pressure during flight, accomplish the following: (a) Within 30 days after the effective date of this AD, accomplish the requirements of paragraphs (a)(1) and (a)(2) of this AD at the lower section of the main baggage bay door in accordance with Jetstream Series 4100 Alert Service Bulletin J41-A52-016, dated May 18, 1993. (1) Measure gap "A", forward and aft of the center line, and record the maximum measurement; measure gap "B", forward and aft of the center line, to determine the location of the maximum gap, and record the maximum measurement and its location; and measure the thickness of the back-up seal at the location of the maximum measurement for gap "B", and record the thickness in accordance with the service bulletin. (2) Perform a detailed visual inspection and an inspection by feel to detect damage and/or adhesion failure of the pressure seal and the back-up seal, and prior to further flight, repair any damaged and/or disbonded seal in accordance with the service bulletin. Repeat this inspection thereafter after the last flight of the airplane each day. (b) Within 10 days after measuring the gaps or finding damage and/or disbonding to the seals, submit a report of any inspection findings, to Jetstream Aircraft, Limited, in accordance with Jetstream Series 4100 Alert Service Bulletin J41-A52-016, dated May 18, 1993. Report gap measurements, and damage and/or disbonding to the seals, to: Customer Support Manager, Jetstream Aircraft Ltd., Prestwick, England; fax 011-44-292-671620. Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056. (c) Within 60 days after the effective date of this AD, install Jetstream Aircraft, Limited, Repair Scheme J41R0370 in accordance with Jetstream Aircraft Limited Drawing 141R0370, Issue 3, dated May 27, 1993. Installation of Jetstream Aircraft, Limited, Repair Scheme J41R0370, constitutes terminating action for the repetitive inspection requirements of this AD. (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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests 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. (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 measurements, inspections, repairs of damaged and/or disbonded seals, recording and reporting requirements shall be done in accordance with Jetstream Series 4100 Alert Service Bulletin J41-A52-016, dated May 18, 1993. The repair scheme shall be done in accordance with Jetstream Aircraft Limited Drawing 141R0370, Issue 3, dated May 27, 1993, which contains the following list of effective pages: Sheet Number Revision Level Shown on Page Date Shown on Page 1, 5-6 3 May 27, 1993 2-4 1 May 14, 1993 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 Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. 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. (g) This amendment becomes effective on August 2, 1993.
47-32-04: 47-32-04 BELL: (Was Mandatory Note 4 of AD-1H-1.) Applies Only to Model 47B Serial Numbers 2 Through 6, 10 Through 17, and 20 Through 22. Compliance required not later than next 25-hour inspection after September 15, 1947. Placard the antitorque rotor blades, "Do Not Use for Handling Helicopter," to warn ground personnel against using the antitorque rotor blades as handholds when hand-maneuvering the rotorcraft on the ground. Mishandling of these blades may cause unseen damage to them, which, in turn, may result in failure of the blades in flight. The stainless steel leading edge should be inspected carefully, particularly near the root, for cracking. (Bell Service Bulletin 47C16 dated March 25, 1947, covers this same subject.)
2010-18-12: We are adopting a new airworthiness directive (AD) for all Robert E. Rust, Jr. Models DeHavilland DH.C1 Chipmunk 21, DH.C1 Chipmunk 22, and DH.C1 Chipmunk 22A airplanes. This AD requires you to do a one-time inspection of the flap operating system for an unapproved latch plate design installation, with replacement as necessary. This AD results from a report of a latch plate failing in service that was not made in accordance with the applicable de Havilland drawing. We are issuing this AD to detect and correct an unauthorized latch plate design installation which could result in an un-commanded retraction of the flaps. This failure could lead to a stall during a landing approach.
91-06-07: 91-06-07 FOKKER: Amendment 39-6924. Docket No. 90-NM-260-AD. Applicability: Certain Model F-28 Mark 0100 series airplanes; Serial Numbers 11244 through 11256, 11259, 11260, 11263, 11268 through 11278, 11280 through 11283, and 11286; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent temperature increase in the contactor studs, smoke in the cockpit, and a potential electrical fire, accomplish the following: A. Within 45 days after the effective date of this AD, perform an inspection of the Electrical Power Center (EPC), the Battery Relay Panel (BRP), contactors, and terminal blocks for insulation sleeve length and washer installation, in accordance with Part 1 and Part 2, as applicable, of the Accomplishment Instructions of Fokker Service Bulletin F100-24-012, dated September 3, 1990. 1. If defects are found, prior to further flight, correct the sleeve length and the washer installation in accordancewith Part 3 of the Accomplishment Instructions of the service bulletin. 2. If no defects are found, or if the corrections required by paragraph A.1 of this AD have been accomplished, accomplish the work completion procedures and perform the operational checks in accordance with Part 4 of the Accomplishment Instructions of the service bulletin before returning the airplane to service. 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 North 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 (39-6924, AD 91-06-07) becomes effective on April 8, 1991.
80-22-09: 80-22-09 COSTRUZIONI AERONAUTICHE GIOVANNI AGUSTA: Amendment 39- 3957. Applies to Model A109A series helicopters, certificated in all categories, except for the following serial numbered helicopters: 7107 7119 7142 7150 7109 7128 7143 7152 7110 7132 7144 7158 7113 7138 7145 7160 7114 7140 7148 7166 and subsequent. 7117 Compliance required as indicated, unless already accomplished. To prevent failure of the engine mount structure, accomplish the following: (a) Within the next 25 hours time in service after the effective date of this AD, and thereafter at intervals not to exceed 25 hours time in service since the last inspection, visually inspect the forward mounting tab of the aluminum engine outer lateral fitting, P/N 109-0320-97- 4, for cracks in accordance with "ACCOMPLISHMENT INSTRUCTIONS" of Costruzioni Aeronautiche Giovanni Agusta Service Bulletin No. 109-18, dated April 27, 1979 (hereinafter referren to as the Service Bulletin), or an FAA-approved equivalent. (b) If, as a result of the inspections required in paragraph (a) of this AD, no cracking is found, return the helicopter to service and continue to inspect in accordance with paragraph (a) or comply with paragraph (d) of this AD. (c) If, as a result of any inspection required in paragraph (a) of this AD, cracking is found, before further flight, except as provided in paragraph (e) of this AD, - - (1) Replace the cracked fitting with a serviceable fitting of the same part number and continue to inspect in accordance with paragraph (a) of this AD; or (2) Replace the cracked fitting with a new steel fitting, P/N 109-0320-97-6, or an FAA-approved equivalent. (d) Compliance with the repetitive inspections required by paragraphs (a), (b) and (c)(1) of this AD may be discontinued when a steel fitting, P/N 109-0320-97-6, or an FAA approved equivalent, is installed. (e) In accordance with FAR Sections 21.197 and 21.199, the helicopter may be flown to a base where the maintenance required by this AD may be accomplished. Ferrying of the helicopter with a failed fitting or an engine inoperative is not permitted. (f) If an equivalent means of compliance is used in complying with paragraphs (a), (c)(2) and (d) of this AD, that equivalent means must be approved by the Chief, Aircraft Certification Staff, AEU-100, Europe, Africa and Middle East Office, FAA, c/o American Embassy, Brussels, Belguim. (g) Upon request of an operator, the Chief, Aircraft Certification Staff, Europe, Africa and Middle East Office, may approve an equivalent modification or replacement fitting provided the request is made through an FAA Maintenance Inspector and the request contains substantiating data to justify the request for that operator. This amendment becomes effective November 6, 1980.