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88-06-02: 88-06-02 CESSNA: Amendment 39-5900. Applicable to Model 550 series airplanes, serial numbers (S/N) 550-0561, -0562, -0564, -0565, -0566, -0568, and -0569; and Model S550 series airplanes, S/N S550-0140 through -0146, -0148, and -0149; certificated in any category. Compliance is required as indicated, unless previously accomplished. To preclude wiring failure, which could result in smoke and/or fire in the cabin, accomplish the following: A. For Cessna Model 550 series airplanes: Prior to next activation of the airplane's electrical power, disconnect the electrical power to the indirect lighting system, in accordance with Cessna Alert Service Letter SLA550-33-02, dated March 14, 1988. Electrical power may be reconnected to the indirect lighting system following replacement of the affected wiring harness described in, and in accordance with, Cessna Service Bulletin SB550-33-9, dated March 17, 1988, or later FAA-approved revisions. B. For Cessna Model S550 series airplanes: Prior to next activation of the airplane's electrical power, disconnect the electrical power to the indirect lighting system, in accordance with Cessna Alert Service Letter SLAS550-33-01, dated March 14, 1988. Electrical power may be reconnected to the indirect lighting system following replacement of the affected wiring harness described in, and in accordance with, Cessna Service Bulletin, SBS550-33-5, dated March 17, 1988, or later FAA-approved revisions. C. An alternate means of compliance which provides an acceptable level of safety may be used when approved by the Manager, Wichita Aircraft Certification Office, FAA, Central Region. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer, may obtain copies upon request to Cessna Aircraft Company, P.O. Box 7706, Wichita, Kansas 67277. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle,Washington, or the FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas. This amendment 39-5900 becomes effective May 10, 1988. It was effective earlier to all recipients of Priority Letter AD 88-06-02, issued March 16, 1988.
99-23-16: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes, that requires repetitive detailed visual inspections to detect cracking of the vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing; and corrective actions, if necessary. This amendment also provides for optional terminating action for the repetitive inspections. 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 vertical flange of the inboard Z-stiffeners of the centerline panel of the fuselage belly fairing, which could result in reduced structural integrity of the belly fairing.
2019-05-05: We are superseding Airworthiness Directive (AD) 97-26-03 for Eurocopter Deutschland GmbH Model MBB-BK 117 A-1, MBB-BK 117 A-3, MBB- BK 117 A-4, MBB-BK 117 B-1, MBB-BK 117 B-2, and MBB-BK 117 C-1 helicopters. AD 97-26-03 required visual inspections for cracks in the ribbed area of the main rotor (M/R) mast flange (flange). Since we issued AD 97-26-03, we have determined that a certain reinforced M/R mast is not affected by the unsafe condition. This new AD retains the requirements of AD 97-26-03 and removes a certain M/R mast from the applicability. The actions of this AD are intended to address an unsafe condition on these products.
98-01-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A330 and A340 series airplanes. This action requires repetitive operational tests of the override mechanism of the trimmable horizontal stabilizer (THS) to determine if the system functions correctly; and corrective action, if necessary. This amendment is prompted by the issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to prevent uncommanded movement of the THS, which could result in reduced controllability of the airplane.
87-16-09: 87-16-09 SHORT BROTHERS PLC: Amendment 39-5698. Applies to Model SD3-60, serial numbers SH3601 through SH3679, certificated in any category. Compliance required within 90 days after the effective date of this AD, unless previously accomplished. To prevent the potential for the loss of recorded information from the flight data recorder, due to corrosion, accomplish the following: A. Install a flight data recorder cover in accordance with the Shorts Service Bulletin No. SD360-31-04, Revision No. 2, dated October 1986. B. Inspect the installed flight data recorder for corrosion of the circuit cards and correct as required in accordance with the appropriate recorder maintenance manual. 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. D. Special flight permits may be issued in accordancewith FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Shorts Aircraft, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. 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 becomes effective September 10, 1987.
89-19-09: 89-19-09 FOKKER: Amendment 39-6323. (Docket No. 89-NM-95-AD) Applicability: Model F-27 series airplanes, Serial Number 10202, 10105 through 10684, 10686, 10687, and 10689 through 10692, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural capability of the fuselage and subsequent decompression of the airplane, accomplish the following: A. For airplanes in post-Service Bulletin F27/21-30 configuration, within 30 days after the effective date of this AD or upon the accumulation of 30,000 landings, whichever occurs later, inspect the external skin at the riveted connections between fuselage Station 1400 and the partial pressure bulkhead, in accordance with Fokker Service Bulletin F27/53-108, dated February 3, 1989. If cracks are found, repair prior to further flight, in accordance with the service bulletin. B. For airplanes in pre-Service Bulletin F27/21-30 configuration, within 30 days after the effective date of this AD, or upon the accumulation of 50,000 landings, whichever occurs later, inspect the external skin at the riveted connections between Fuselage Station 1400 and the partial pressure bulkhead in accordance with Fokker Service Bulletin F27/53-108 dated February 3, 1989. If cracks are found, repair prior to further flight, in accordance with the service bulletin. 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 will either 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 Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, C-68966, Seattle, Washington 98168. This amendment (39-6323, AD 89-19-09) becomes effective on October 14, 1989.
98-25-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) T98-25-51 that was sent previously to all known U.S. owners and operators of certain Airbus Model A310 and A300-600 airplanes by individual telegrams. This AD requires deactivation of both thrust reversers and a revision of the Airplane Flight Manual (AFM) to ensure that safe and appropriate performance is achieved during certain takeoff conditions. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent inflight deployment of a thrust reverser, which could result in reduced controllability of the airplane.
86-20-06: 86-20-06 BELL HELICOPTER TEXTRON, INC.: Amendment 39-5427. Applies to Bell Helicopter Textron, Inc., Model 214ST helicopters, S/N's 28101 through 28159, and Models 214B and 214B-1, S/N's 28001 through 28070, certificated in any category, equipped with main rotor drag brace assembly P/N 214-010-113-001. Compliance is required as indicated, unless already accomplished. (a) To prevent failure of the M/R drag brace assembly, P/N 214-010-113-001, on the Model 214ST helicopter, replace it with M/R drag' brace assembly, P/N 214-010-113-105, within the next 50 hours' time in service or within 30 days after the effective date of this AD, whichever comes first. (b) To prevent failure of the M/R drag brace assembly, P/N 214-010-113-001 on the Model 214B and 214B-1 helicopters, replace it with M/R drag brace assembly, P/N 214-010-113- 107, within the next 50 hours' time in service or within 30 days after the effective date of this AD, whichever comes first. (c) An alternate method of compliance which provides an equivalent level of safety with this AD may be used when approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. This amendment becomes effective October 18, 1986.
98-13-07: This amendment adopts a new airworthiness directive (AD) that applies to certain Industrie Aeronautiche e Meccaniche (I.A.M.) Model Piaggio P-180 airplanes. This AD requires accomplishing a leakage check of all lavatory water tube/hose connections, and correcting the installation of these connections if leakage is found. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Italy. The actions specified by this AD are intended to prevent water leakage from the lavatory water duct system, which could collect in the fuselage, freeze in cold weather conditions, and cause the rudder control system to jam.
89-17-05: 89-17-05 BELL HELICOPTER TEXTRON, INC.: Amendment 39-6276. Applicability: Model 222, 222B, and 222U helicopters, certificated in any category, with horizontal stabilizer assembly, Part Number (P/N) 222-035-250-101, -103, or -105, installed. (Docket No. 89-ASW-16) Compliance: Required within the next 50 hours' time in service for horizontal stabilizer assemblies with more than 2,100 hours' time in service; compliance for horizontal stabilizers with less than 2,100 hours' time in service is required prior to the accumulation of 2,150 hours' time in service; and both thereafter at intervals not to exceed 300 hours' time in service. To prevent failure of the horizontal stabilizer assembly, which could result in loss of the helicopter, accomplish the following: (a) Perform the Part "A" of the "Accomplishment Instructions" of BHTI Alert Service Bulletin (ASB) No. 222-89-53, dated March 20, 1989, for the Model 222 and 222B; or ASB No. 222U-89-27, dated March 20,1989, for the Model 222U. (b) If a crack is detected, remove and replace with a serviceable horizontal stabilizer assembly prior to further flight. (c) The requirements of this AD do not apply if horizontal stabilizer assembly P/N 222-035-250-107 is installed for the Model 222 or P/N 222-035-250-109 is installed for the Models 222B and 222U. (d) An alternate method of compliance which provides an equivalent level of safety, may be approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170. The inspection procedures shall be done in accordance with Part "A" of the "Accomplishment Instructions" of BHTI Alert Service Bulletin (ASB) No. 222-89-53, dated March 20, 1989, for the Model 222 and 222B; or ASB No. 222U-89-27, dated March 20, 1989, for the Model 222U. This incorporation by reference of ASB No 222-89-53 and ASB No. 222U-89-27, both dated March 20, 1989, 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 Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, Texas 76101. Copies may be inspected at the Office of the Assistant Chief Counsel, Southwest Region, 4400 Blue Mound Road, Room 158, Building 3B, Fort Worth, Texas, between 8 a.m. and 4 p.m. weekdays, except Federal holidays, or at the Office of the Federal Register, 1100 L Street, N.W., Room 8301, Washington, D.C. This amendment (39-6276, AD 89-17-05) becomes effective on August 28, 1989.