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2019-03-02: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued 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 an incorrect size bolt may have been used to assemble the elevator bellcrank pivot joint. We are issuing this AD to require actions to address the unsafe condition on these products.
94-18-07: This amendment supersedes two existing airworthiness directives (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes and certain Model MD-11 series airplanes, that currently require inspections to determine the serial numbers and to detect defects in the upper and lower lock links on the nose landing gear (NLG), and rework or replacement of any defective link with a serviceable link. This amendment requires additional inspections and provides optional terminating action for those inspections. This amendment is prompted by additional reports of defects found on links that are required to be inspected by the existing AD's. The actions specified in this AD are intended to prevent collapse of the NLG.\n\n\tThe incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of September 15, 1994.\t\n\tComments for inclusion in the Rules Docket must be received on or before October 31, 1994.
88-08-03: 88-08-03 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-5886. Applies to all Aerospatiale Model SA 365N series helicopters certificated in all categories. Compliance is required as indicated (unless already accomplished). To prevent failure of the attachment bolts of the spherical thrust bearings, accomplish the following: (a) Replace attachment beam bolts (P/N 365A31-1898-20) for the spherical thrust bearings as follows -- (1) For bolts which have 900 or more hours' time in service on the effective date of this AD, replace the bolts within the next 100 hours' time in service; and (2) For bolts which have less than 900 hours' time in service on the effective date of this AD, replace the bolts before they reach 1,000 hours' time in service. (b) An alternate method of compliance with this AD, which provides an equivalent level of safety, may be used when approved by the Manager, Aircraft Certification Division, Federal Aviation Administration, Fort Worth, Texas 76193-0100, or by the Manager, Aircraft Certification Office, AEU-100, FAA, Europe, Africa, and Middle East Office, c/o American Embassy, Brussels, Belgium. (c) In accordance with FAR 21.197 and 21.199, flight is permitted to a base where the maintenance required by this AD may be accomplished. NOTE: Aerospatiale Service Bulletin No. 01.20 pertains to this subject. This amendment, 39-5886, becomes effective April 29, 1988.
86-10-07: 86-10-07 SHORT BROTHERS, LTD.: Amendment 39-5302. Applies to certain Model SD3-60 airplanes, as described in Short Brothers, Ltd., Service Bulletin SD360-32-19, dated March 1985, certificated in any category. To prevent the failure of the nose landing gear main fitting, accomplish the following within 90 days after the effective date of this AD, unless previously accomplished: 1. Inspect using eddy current methods and rework, as necessary, the main fitting of the nose landing gear in accordance with Dowty Rotol Service Bulletin 32-26SD, dated December 19, 1984. 2. 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. 3. 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 bythis 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 Short Brothers Aircraft, 2011 Crystal Drive, 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 June 16, 1986.
2019-03-04: We are superseding Airworthiness Directive (AD) 2018-11-16 for all Engine Alliance (EA) GP7270 and GP7277 turbofan engines with a certain engine fan hub assembly. AD 2018-11-16 required a one-time eddy current inspection (ECI) of the engine fan hub blade slot bottom and blade slot front edge for cracks, a visual inspection of the engine fan hub assembly for damage, and removal of parts if damage or defects are found that are outside serviceable limits. This AD retains these requirements, but expands the population of affected engine fan hub assemblies and revises the compliance time for the inspections. This AD was prompted by the FAA's determination that inspections need to be expanded to all EA GP7270 and GP7277 turbofan engines. We are issuing this AD to address the unsafe condition on these products.
2000-15-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), and DC-9-87 (MD-87); Model MD-88 airplanes; and Model MD-90-30 series airplanes; that requires installation of a pipe support and clamps on the hydraulic lines in the aft fuselage; replacement of the hydraulic pipe assembly in the aft fuselage with a new pipe assembly; and installation of drain tube assemblies and diverter assemblies in the area of the auxiliary power unit (APU) inlet; as applicable. This amendment is prompted by reports of smoke and odor in the passenger cabin and cockpit due to hydraulic fluid leaking into the APU inlet, and subsequently, into the air conditioning system. The actions specified by this AD are intended to prevent such hydraulic fluid leakage due to fatigue vibration and cracking in the flared radius of a hydraulic pipe in the aft fuselage, which could result in smoke and odors in the passenger cabin or cockpit.
97-20-13: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 97-20-13 which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland Model EC135 P1 and T1 helicopters by individual letters. This amendment is prompted by the discovery of cracks on the stator blades of the fenestron tail rotor (tail rotor). The actions specified by this AD are intended to prevent failure of the tail rotor and subsequent loss of control of the helicopter.
89-07-03: 89-07-03 SHORT BROTHERS, PLC: Amendment 39-6159. Applicability: Model SD3-30 series airplanes, equipped with Menasco nose landing gear, Part No. 18001, having nose landing gear Serial Numbers 017 through 097 with pintle pins P/N 18109-3 or 18110-3 installed, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent collapse of the nose landing gear, accomplish the following: A. Prior to the accumulation of 30,000 landings on the nose landing gear pintle pins, or within the next 250 landings after the effective date of this AD, whichever occurs later, and thereafter at intervals not to exceed 30,000 landings, replace nose landing gear pintle pins, part number (P/N) 18109-3 and 18110-3 pintle pins, in accordance with Short Service Bulletin SD330- 32-119, dated February 1988. NOTE: Shorts Service Bulletin SD330-32-119 references Menasco Service Bulletin 32- 69, dated August 11, 1981, for instructions for accomplishing the pintle pin replacement. 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. 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. 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 documents from the manufacturer may obtain copies upon request to Short Brothers PLC, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. 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 (39-6159, AD 89-07-03) becomes effective April 26, 1989.
88-18-06: 88-18-06 MORAVAN: Amendment 39-5994. Applies to Model ZLIN 526L (all serial numbers) airplanes certificated in any category. Compliance: Required within the next 100 hours time-in-service (TIS) after the effective date of this AD and every 100 hours TIS thereafter, unless already accomplished. To preclude structural airframe failure, accomplish the following: (a) Visually inspect, using a 3-power magnifying glass, the forward portion of the cabin area tubular structure around the airplane leveling points, for cracks using supplementary lighting as required in accordance with MORAVAN Mandatory Service Bulletin Z526L, dated July 30, 1987. If a crack is found, before further flight repair the crack in accordance with instructions from MORAVAN approved by the Manager, Aircraft Certification Staff, AEU-100. (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 beused if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B- 1000 Brussels, Belgium. All persons affected by this directive may obtain copies of the document referred to herein upon request to Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B-1000 Brussels, Belgium; or MORAVAN National Corp., 765-81 Otrokovice, Czechoslovakia; or may examine this document at the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-5994, becomes effective on September 8, 1988.
79-20-08: 79-20-08 GREAT LAKES: Amendment 39-3580. Applies to Models 2T-1A-1 and 2T- 1A-2 airplanes having a Lycoming IO-360-B1F6 or AIO-360-B1G6 engine installed. \n\n\tCOMPLIANCE: Required as indicated unless already accomplished. \n\n\tTo preclude engine induction system blockage by pieces of failed alternate air doors and resulting power loss, accomplish the following: \n\n\tA)\tWithin the next 25 hours time-in-service after the effective date of this AD: \n\n\t\t1.\tVisually inspect the aircraft induction system drain fitting located in the induction elbow below the fuel injector for blockage or restriction. If the hole is restricted in the weld area or not drilled through the elbow, before further flight open up the restricted hole or drill a hole in the elbow at the fitting location using a No. 10 (.193) drill. \n\n\tB)\tWithin 25 hours time-in-service after the effective date of this AD and each 100 hours time-in-service thereafter: \n\n\t\t1.\tVisually inspect the alternate air door for distortion, heat damage and cracks. If any of these conditions are noted, before further flight repair the existing door or fabricate and install a new door in accordance with Figure I of this AD. \n\n\t\t2.\tVisually inspect the induction system including the filter for cleanliness, security and damage from backfire or induction system fires. Before further flight, repair or replace any damaged components necessary to restore the system to an airworthy condition. \n\n\tC)\tAny equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tThis amendment becomes effective on October 8, 1979. \n\n\nFIGURE 1