Results
98-24-32: This amendment adopts a new airworthiness directive (AD) that is applicable to Eurocopter France Model AS-365N2, SA-360C, SA-365C, C1, C2, N, N1, and SA-366G1 helicopters. This action requires inspecting for broken or out-of-tolerance attachment springs on the tail rotor hub fairing (fairing), replacing broken attachment springs and attachment springs that are out-of-tolerance, and marking the fairing to indicate compliance with this AD. This amendment is prompted by three in-service reports of failed attachment springs. The actions specified in this AD are intended to prevent failure of an attachment spring, which could cause loss of the fairing, damage to the tail rotor, and subsequent loss of control of the helicopter.
86-25-05: 86-25-05 SIKORSKY AIRCRAFT: Amendment 39-5471. Applies to Model S-58A, B, C, D, E, F, G, H, J, BT, DT, ET, FT, HT, and JT, CH-34 series, HH-34 series, SH-34 series, UH- 34 series, and VH-34 series helicopters certificated in any category and fitted with tail rotor intermediate gearbox input bevel pinions Part Number (P/N) S1635-64114-0 and output bevel gears P/N S1635-64115-0. (See Note 1 for exempt pinion and gear configurations.) Compliance is required as indicated, unless already accomplished. (a) To preclude failure of pinions or gears identified above, accomplish the following: (1) For applicable pinions or gears that have attained 750 or less hours' time in service on the effective date of this AD, replace with a serviceable pinion or gear as required, prior to their accumulation of 1,000 hours' time in service. (2) For pinions or gears that have attained more than 750 hours' time in service on the effective date of this AD, replace with a serviceablepinion or gear as required, within the next 250 hours' time in service. (3) Operators who have not kept records of hours' time in service on individual intermediate gearbox bevel gears and bevel pinions shall substitute rotorcraft hours' time in service in lieu thereof. NOTE 1. This AD is not applicable to helicopters fitted with tail rotor intermediate gears which utilize the following pinion and gear combinations: (a) P/N 1635-64114-101 pinion and P/N S1635-64115-101 gear. (b) P/N 1635-64114-102 pinion and P/N S1635-64115-102 gear. (c) P/N 1635-64114-0 pinion and P/N S1635-64115-0 gear reworked in accordance with Sikorsky Service Bulletin 58B35-26. This rework includes remarking P/N S1635-64114-0 pinion and P/N S1635-64115-0 gear with TS-200-1 and TS-200-2, respectively. NOTE 2. Refer to the Equalized Inspection and Maintenance Program Manual SA 4047-20, Revision 10, dated December 14, 1984, or later FAA-approved revision for retirement times assigned tonew or modified bevel pinions and bevel gears for the Model S-58BT, DT, ET, FT, HT, and JT helicopters, and to the Maintenance Manual SA 4045-15 Section IV, revised December 14, 1984, or later FAA-approved revision for retirement times assigned to new or modified bevel pinions and gears for the Model S-58A, B, C, D, E, F, G, H, and J helicopters. Upon request, an alternate method of compliance which provides an equivalent level of safety may be approved by the Manager, Boston Aircraft Certification Office, ANE-150, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Boston Aircraft Certification Office, ANE-150, FAA, 12 New England Executive Park, Burlington, Massachusetts 01803 may adjust the compliance time specified in this AD. This amendment becomes effective on January 5, 1987.
52-01-07: 52-01-07 BELL: Applies to All Model 47D1 Helicopters Having 47-661-030-1 Hub Assembly in the Cooling Fan. Refer to Bell Service Bulletin No. 72. Compliance required at the next 300-hour overhaul, but not later than March 1, 1952. To reduce the possibility of throwing blades in flight, rework the existing 47-661-030-1 hub and reassemble the fan using the parts provided in the modification kit. (Note: Do not install old fan blades.) Balance modified fan assembly (assigned P/N 47-661-036-5) in accordance with specified erection and maintenance procedure prior to installation. (Bell Service Bulletin No. 82 covers this same subject.)
2013-10-52: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-110B1 and GE90-115B turbofan engines. This emergency AD was sent previously to all known U.S. owners and operators of these engines. This AD prohibits operation of an airplane with affected transfer gearbox assemblies (TGBs) installed on both engines five days after the effective date of this AD. This AD was prompted by reports of two failures of TGBs which resulted in in-flight shutdowns (IFSDs). We are issuing this AD to prevent additional IFSDs of one or more engines, loss of thrust control, and damage to the airplane.
2010-14-03: We are superseding an existing 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 in-flight test deployments, several Air-Driven generators (ADGs) failed to come on-line. Investigation revealed that, as a result of a wiring anomaly that had not been detected during ADG manufacture, a short circuit was possible between certain internal wires and their metallic over-braided shields, which could result in the ADG not providing power when deployed. * * * The unsafe condition is failure of the ADG, which could lead to loss of several functions essential for safe flight. We are issuing this AD to require actions to correct the unsafe condition on these products.
98-24-30: This amendment adopts a new airworthiness directive (AD) that applies to certain Stemme GmbH & Co. KG (Stemme) Models S10, S10-V, and S10-VT sailplanes. This AD requires inspecting certain areas in the flight control system for cracks; immediately replacing any cracked parts; and eventually replacing all longitudinal coupling with modified coupling regardless if found cracked. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct cracks in certain areas of the flight control system, which could result in flight control system failure with consequent reduced or loss of control of the sailplane.
2013-12-01: We are adopting a new airworthiness directive (AD) for all Rolls-Royce plc (RR) model RB211 Trent 768-60, 772-60, and 772B-60 turbofan engines. This AD was prompted by low-pressure (LP) compressor blade partial airfoil release events. This AD requires a one-time ultrasonic inspection of LP compressor blades that had accumulated more than 2,500 flight cycles (FC) since new. We are issuing this AD to prevent LP compressor blade airfoil separations, engine damage, and damage to the airplane.
2010-13-04: 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: Two in-service incidents have been reported on DHC-8 Series 400 aircraft in which the nose landing gear (NLG) trailing arm pivot pin retention bolt (part number NAS6204-13D) was damaged. One incident involved the left hand NLG tire which ruptured on take-off. Investigation determined that the retention bolt failure was due to repeated contact of the castellated nut with the towing device including both the towbar and the towbarless rigs. The loss of the retention bolt allowed the pivot pin to migrate from its normal position and resulted in contact with and rupture of the tire. The loss of the pivot pin could compromise retention of the trailing arm andcould result in a loss of directional control due to loss of nose wheel steering. The loss of an NLG tire or the loss of directional control could adversely affect the aircraft during take off or landing. * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.
98-24-29: This amendment adopts a new airworthiness directive (AD) that applies to all Aerostar Aircraft Corporation (Aerostar) PA-60-600 and PA-60-700 series airplanes. This AD requires repetitively inspecting the forward face of each wing s 55-percent upper spar cap for cracks above the main landing gear fitting in the top of the wheel well, and replacing or repairing any cracked upper spar cap. Reports of spanwise cracks in the area above the main landing gear attachment on two of the affected airplanes prompted this action. The actions specified by this AD are intended to detect and correct fatigue cracking of the wing upper spar cap, which could result in structural failure of the wing spar to the point of failure with consequent loss of control of the airplane.
93-24-13: 93-24-13 THE ENSTROM HELICOPTER CORPORATION: Amendment 39-8968. Docket Number 93-SW-24-AD. Applicability: Model F-28C, F-28C-2, F-28F, 280C, 280F, and 280FX series helicopters, equipped with a 24 volt D.C. electrical system, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent failure of the trim motor relay that could result in full deployment of the trim system, high cyclic control forces, and loss of control of the helicopter, accomplish the following: (a) Within the next 5 hours' time-in-service (TIS) after the effective date of this airworthiness directive (AD), inspect the trim motor, wiring, and relays (trim system) for failure in accordance with the Compliance Section of The Enstrom Helicopter Corporation Service Directive Bulletin No. 0082 (SDB 0082), Revision A, dated March 18, 1993. (1) Rewire the trim system and replace the trim actuator circuit breaker in accordance with paragraph 5.3 ofSDB 0082, Revision A, dated March 18, 1993, to preclude trim overtravel. (2) After rewiring the trim system in accordance with paragraph (a)(1) of this AD, verify proper operation of the trim system and the limit switch stop position in accordance with the applicable maintenance manual. (b) When installing a replacement or zero-time relay or circuit breaker, install in accordance with paragraph 5.3 of SDB 0082, Revision A, dated March 18, 1993. After wiring the trim system in accordance with SDB 0082, Revision A, dated March 18, 1993, verify proper operation of the trim system at the limit switch stop position in accordance with the applicable maintenance manual. (c) Inspect the trim system for failure in accordance with the Compliance Section of SDB 0082, Revision A, dated March 18, 1993, at intervals not to exceed 100 hours' TIS from the last inspection or at each annual inspection, whichever occurs first. (d) Replace any unairworthy trim system part with an airworthy part in accordance with the applicable maintenance manual. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used when approved by the Manager, Chicago Aircraft Certification Office, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Chicago Aircraft Certification Office. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Chicago Aircraft Certification Office. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the helicopter to a location where the requirements of this AD can be accomplished. (g) The inspection, rewiring, and replacement shall be done in accordance with The Enstrom Helicopter Corporation Service Directive Bulletin No. 0082, Revision A, dated March 18, 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 The Enstrom Helicopter Corporation, Twin County Airport, P.O. Box 490, Menominee, Michigan 49858. Copies may be inspected at the FAA, Office of the Assistant Chief Counsel, 2601 Meacham Boulevard, Room 663, Fort Worth, Texas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on August 26, 1994, to all persons except those persons to whom it was made immediately effective by Priority Letter AD 93-24-13, issued December 6, 1993, which contained the requirements of this amendment.