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2015-21-07: We are adopting a new airworthiness directive (AD) for certain Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, A340- 300, A340-500, and A340-600 series airplanes. This AD requires a detailed inspection of the girt installation of each escape slide and slide raft, and corrective action if necessary. This AD was prompted by a report of incorrect installation of the girt panel on passenger doors and an incorrectly installed quick release (girt) bar into the [[Page 63081]] girt panel of the slide raft. We are issuing this AD to detect and correct incorrect girt installation of the escape slide and slide raft, which could prevent slide deployment during an emergency, and result in reduced evacuation capacity from the airplane and possible injury to occupants.
88-17-03: 88-17-03 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-5943. Applies to IO-520- BA, BB, IO-550-B, and TSIO-520-BE, LB, UB, and WB series engines equipped with air conditioners. Compliance is required as specified in the body of the AD, unless already accomplished. To prevent possible starter adapter shaftgear assembly failure, accomplish the following: (a) Before further flight, remove the top engine cowl and gain access to the air conditioner (freon compressor) drive pulley and with a light and mirror, determine if the sheave attach nut is a steel locking type (Reference paragraph II of TCM Service Bulletin (SB) M87-24, dated December 15, 1987). (1) If the nut is a steel locking type, remove the freon compressor drive belt. (2) If the nut is castellated, determine via log books and maintenance records that the castellated nut is the original nut and has not been substituted for a steel locking type nut. (i) If the castellated nut is the original, no further action is required. (ii) If the castellated nut is not the original, but a substitution for the original installed steel locking type nut, remove the freon compressor drive belt. (iii) If it cannot be determined that the castellated nut is the original, remove the freon compressor drive belt. NOTE: Compliance with paragraph (b) below before further flight, may be accomplished in lieu of paragraph (a) above. (b) Within the next 25 flight hours, after the effective date of this AD, remove the starter adapter assembly (starter drive assembly) and replace in accordance with the following table: Engine Model Replacement Starter Drive Assembly P/N IO-520-BA, BB, IO-550-B 642087A23R TSIO-520-LB, WB 642087A22R TSIO-520-BE 642087A24R TSIO-520-UB 646757A4R NOTE: Return the starter drive assembly (less drive sheave) to the manufacturer for replacement. (1) Install the replacement assembly in accordance with paragraph 3 of TCM SB M88-5, dated April 4, 1988, and appropriate maintenance manuals. (2) Install the drive belt and insure proper alignment of the sheaves in accordance with paragraphs 1 through 3 of TCM SB M88-6, dated April 4, 1988. (c) Replace top engine cowl. (d) Make appropriate log book entry showing compliance with this AD. NOTE: Compliance with AD 87-14-02 issued against the starter drive assembly is not required when compliance with this AD is accomplished. (e) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (f) Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Atlanta Aircraft Certification Office, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. (g) Upon submission of substantiating data by an owner or operator, through an FAA maintenance inspector, the Manager, Atlanta Aircraft Certification Office, may adjust the compliance time specified in this AD. NOTES: 1. New or rebuilt TSIO-520-BE engines (used on Piper PA46-310P Malibu) shipped from TCM as a replacement engine in conjunction with compliance to AD 87-26-08 (TCM SB M87-25) should not order a replacement starter drive assembly as these engines already have the replacement starter drive assembly installed. 2. Installation of the replacement starter drive assembly on the TSIO-520-BE engine (used on Piper PA46-310P Malibu) does not require engine removal (Piper Aircraft Corporation SB 876B refers to this subject). TCM SB M88-5, dated April 4, 1988, and TCM SB M88-6, dated April 4, 1988, identified and described in this document, are incorporated herein and made a 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 Teledyne Continental Motors, P.O. Box 90, Mobile, Alabama 36601. The documentsmay also be examined at the Office of the Regional Counsel, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 87-ANE-46, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except federal holidays. This amendment supersedes AD 87-26-01, Amendment 39-5882. This amendment, 39-5943, becomes effective on August 10, 1988.
69-19-01: 69-19-01 PILATUS: Amdt. 39-822. Applies to Model PC-6 Airplanes, Serial Nos. 1 through 701, 2001 through 2018, 2023, 2025 through 2029, 2040 and 2041. Compliance: Required within the next 300 hours' time in service after the effective date of this AD, unless already accomplished. To prevent rotation of pivot bolt P/N 6203.25 located at the hatch door operating bellcrank, replace with a new pivot bolt P/N 112.40.06.120 in accordance with Pilatus Service Bulletin No. 88, dated December 1968, or later Swiss Federal Air Office-approved issue, or an FAA-approved equivalent. This amendment becomes effective September 20, 1969.
2002-11-04: This amendment supersedes an existing airworthiness directive (AD), applicable to all Airbus Model A300 B4-600, A300 B4-600R, and A300 F4-600R series airplanes (A300-600), that currently requires an inspection to detect cracks of certain attachment holes; and installation of new fasteners and follow-on inspections or repair if necessary. This amendment requires repetitive inspections to detect cracks of certain attachment holes, installation of new fasteners, follow-on inspections or repair if necessary, and modification of the angle fittings of frame FR47. This amendment revises the applicability of the existing AD. The actions specified by this AD are intended to prevent fatigue cracking of the forward fitting of fuselage frame FR47, which could result in reduced structural integrity of the frame.
70-14-01: 70-14-01 BELL: Amdt. 39-1022 as amended by Amendment 39-1065. Applies to all Bell Model 47D-1, 47G, 47G-2, and 47H-1 helicopters certificated in all categories and to any other helicopters equipped with duplex pitch change bearings, P/N 47-641-131-1. Compliance required as indicated. To prevent possible failure of tail rotor duplex pitch change bearing and to correct any improper installation of the duplex bearing and delta hinge bolts: (a) Inspect all duplex pitch change bearings within the next 50 hours time in service after the effective date of this AD, unless already accomplished, as follows: (1) Remove tail rotor assembly. (2) Remove and disassemble the tail rotor drive head assembly to expose the duplex bearings and guide sleeve, P/N 47-641-040 or 47-641-130. (3) Inspect the outside surface of the guide sleeve for scoring. (4) Inspect the duplex bearing for roughness. (5) Replace the duplex bearing before further flight as specified in subparagraphs (b)(3) and (4) if the guide sleeve is scored or if the bearing is rough. (6) Install the tail rotor assembly and check rigging and tracking as described in subparagraph (b)(5). (b) Remove and replace duplex pitch change bearings with 450 or more hours time in service on the effective date of this AD within the next 150 hours time in service, as follows: (1) Remove tail rotor assembly, (2) Remove and disassemble the tail rotor drive head assembly, (3) Assemble and install the tail rotor drive head assembly, using a new duplex bearing, P/N 47-641-131-1, in accordance with the procedures specified in Paragraphs 6.63(j) and (k) in the Model 47D-1, 47G, and 47G-2 Maintenance and Overhaul Instruction Manual, as revised August 15, 1961, or in accordance with FAA approved equivalent procedures. (4) Lubricate the bearing and sleeve with grease, MIL-G-25537 or equivalent. (5) Install the tail rotor assembly and check rigging and tracking in accordance with the procedures specified in Paragraphs 6-17(a) through (h) or 6-18(a) through (g) of the appropriate manual or in accordance with FAA approved equivalent procedures. (c) Remove and replace duplex pitch change bearings with less than 450 hours time in service on the effective date of this AD prior to accumulating 600 hours time in service, in accordance with the procedures described in subparagraphs (b)(1) through (5) above. (d) Remove and replace all replacement duplex pitch change bearings prior to accumulating 600 hours time in service. Amendment 39-1022 effective August 10, 1970. This Amendment (39-1065) becomes effective August 17, 1970.
2015-18-04: We are adopting a new airworthiness directive (AD) for certain CFM International S.A. (CFM) CFM56-7B and CFM56-3 turbofan engines. This AD was prompted by a report of an uncommanded in-flight shutdown (IFSD) on a CFM CFM56-7B engine following rupture of the 73-tooth gearshaft located in the engine accessory gearbox (AGB). This AD requires AGB/transfer gearbox (TGB) magnetic chip detector (MCD) inspection of the affected gearshafts until removal. We are issuing this AD to prevent failure of certain engine AGB gearshafts, which could lead to failure of one or more engines, loss of thrust control, and damage to the airplane.
98-10-13: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 series airplanes, that requires modification of the aft avionic fan. 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 prevent failure of the aft avionic fan due to inadequate cooling airflow through the fan housing, which could result in failure of the avionics equipment.
2002-10-14: This amendment adopts a new airworthiness directive (AD) that is applicable to Bombardier-Rotax GmbH 914 F series reciprocating engines. This action requires initial and repetitive inspections of certain exhaust bend assemblies, which are located between the cylinder heads and exhaust manifold assembly. This amendment is prompted by reports of cracks found in exhaust bend assemblies. The actions specified in this AD are intended to prevent carbon monoxide from entering the cabin and also to prevent the possibility of an engine fire.
73-20-05: 73-20-05 de HAVILLAND: Model DHC-6. Amdt. 39-1725. Applies to de Havilland Model DHC-6 Twin Otter Floatplanes, all Series, certificated in all categories, equipped with Canadian Aircraft Products Model 12000A or 12000B Floats installed prior to Float Serial No. 71. 1. Compliance is required within the next ten hours in service from the effective date of this Airworthiness Directive, unless already accomplished. To prevent loosening and subsequent pullout failure of certain float to fuselage bolts, comply with accomplishment instruction of de Havilland Service Bulletin 6/296, Revision A, dated May 11, 1973, or an equivalent alteration approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective October 3, 1973.
65-28-04: 65-28-04 MAULE: Amdt. 39-166 Part 39 Federal Register December 14, 1965. Applies to Model M-4-210 Airplanes, Serial Number 1001 through 1035. Compliance required within the next 100 hours' time in service after the effective date of this AD unless already accomplished. To prevent loss of engine power due to fuel starvation, modify the fuel system in accordance with Maule Service Letter No. 7, dated June 15, 1965, or later FAA-approved revision, or an equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Central Region. This directive effective January 13, 1966.