Results
2005-12-51: The FAA is adopting a new airworthiness directive (AD) for Rockwell International (Aircraft Specification No. A-2-575 previously held by North American and recently purchased by Boeing) Models AT-6 (SNJ-2), AT-6A (SNJ-3), AT-6B, AT-6C (SNJ-4), AT-6D (SNJ-5), AT-6F (SNJ-6), BC-1A, SNJ-7, and T-6G airplanes; and Autair Ltd. (Aircraft Specification No. AR-11 previously held by Noorduyn Aviation Ltd.) Model Harvard (Army AT-16) airplanes. This AD contains the same information as emergency AD 2005-12-51 and publishes the action in the Federal Register. It requires immediate and repetitive inspections of the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of both wings for fatigue cracks; and, if any crack is found, replacement of the cracked angle with a new angle. This AD is the result of a report of a Rockwell International Model SNJ-6 (AT-6F) airplane crash that occurred on May 9, 2005, resulting in two fatalities. We are issuing this AD todetect and correct any fatigue crack in the inboard and outboard, upper and lower wing attach angles (except for the nose angles) of either wing, which could result in failure of the wing. This failure could lead to loss of control of the aircraft.
97-05-11 R1: This amendment revises an existing airworthiness directive (AD), applicable to AlliedSignal Inc. ALF502 and LF507 series turbofan engines, that currently requires initial and repetitive inspections of the oil system chip detectors and oil filter bypass valve, and optional installation of an improved oil filter bypass valve, to ensure the integrity of the reduction gear system and overspeed protection system. This amendment adds an initial inspection threshold for the oil maintenance requirements that was inadvertently omitted from AD 97-05-11, and makes editorial corrections. Paragraphs (b) through (f) of AD 97-05-11 have been rearranged in this AD to make these corrections. This amendment is prompted by the inadvertent omission of the initial inspection threshold. The actions specified by this AD are intended to prevent No. 4 and 5 duplex bearing failure, which can result in a Stage 4 low pressure turbine (LPT) rotor failure, an uncontained engine failure, and damage tothe aircraft.
74-18-04: 74-18-04 BEECH: Amendment 39-1938. Applies to Model A100 (Serial Numbers B-90 through B-92, B-94 through B-102, B-104, B-105, B-107 through B-109, B-111, B-115, B-116, B-118, B-119 and B-121 through B-204) airplanes (except any aircraft serials listed which are equipped with the optional 300 ampere generator system). Compliance: Required as indicated, unless already accomplished. To prevent the fuel transfer sump drain line tube assemblies from contacting the reverse current diode heat sink, accomplish the following: A) Prior to further flight, visually inspect the fuel transfer sump drain line tube assemblies (P/N 100-920001-113 LH and P/N 100-920001-114 RH) for a minimum separation of one-half inch between the fuel transfer sump drain line tube assemblies and the reverse current diode heat sink, located in the aft landing gear wheel wells. Hand form and temporarily support the fuel transfer sump drain line tube assemblies with suitable clamps and/or brackets as necessary to maintain this separation. B) Within 200 hours' time-in-service after the effective date of this AD, remove existing fuel transfer sump drain line tube assemblies (P/N 100-920001-113 LH and P/N 100- 920001-114 RH) and install new fuel transfer sump drain line tube assemblies (P/N 100-920001- 205 LH and P/N 100-920001-206 RH) in accordance with Beech Service Instruction 0668-281 or subsequent revisions. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective August 30, 1974.
87-05-06: 87-05-06 CASA: Amendment 39-5561. Applies to CASA Model C-212 series airplanes listed in CASA Service Bulletin 212-76-04, dated October 23, 1985, certificated in any category. Compliance is required within 11 months after the effective date of this AD. To prevent the partial loss of controllability of the airplane due to an uncontrollable propeller, accomplish the following, unless previously accomplished: A. Modify the propeller feathering control system in accordance with CASA Service Bulletin 212-76-04, dated October 23, 1985. 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. 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 the modification 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 Construcciones Aeronauticas S.A., Getafe, Madrid, Spain. 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 March 25, 1987.
2005-14-08: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-100, -200, -300, and 747SP series airplanes. That AD currently requires certain inspections to find missing or alloy-steel taperlock fasteners (bolts) in the diagonal brace underwing fittings, and corrective actions if necessary. For airplanes with missing or alloy-steel fasteners, that AD also mandates replacement of certain fasteners with new fasteners, which constitutes terminating action for certain inspections. This new AD expands the applicability to include additional airplane models and requires a new inspection to determine fastener material and to find missing or broken fasteners, and related investigative/corrective actions if necessary. This AD is prompted by reports indicating that cracked fasteners made of A286 material were found on airplanes that had only fasteners made of A286 material installed in the area common to the diagonal brace underwing fittings.We are issuing this AD to prevent loss of the underwing fitting load path due to missing or damaged alloy-steel or A286 taperlock fasteners, which could result in separation of the engine and strut from the airplane. \n\n\nDATES: This AD becomes effective August 15, 2005. \n\n\tThe incorporation by reference of Boeing Alert Service Bulletin 747-57A2312, Revision 1, dated April 29, 2004, is approved by the Director of the Federal Register as of August 15, 2005. \n\n\tOn August 1, 2001 (66 FR 34094, June 27, 2001), the Director of the Federal Register approved the incorporation by reference of Boeing Alert Service Bulletin 747-57A2312, dated June 15, 2000.
75-12-05: 75-12-05 MCCLISH (Funk): Amendment 39-2225: Applies to all McClish (Funk) Model B, B75L, B85C and Funk C Aircraft. 1. Affects wing forward external support struts and rear fuselage lower longerons at the tail post. a. Within the next ten hours' time in service or one month, whichever occurs first, after the effective date of this Airworthiness Directive, unless accomplished within the last 90 hours in service or 11 months, accomplish the following: b. Inspect the wing forward external support struts at the lower end where the aileron cable enters the strut, for corrosion and cracks. c. Inspect the lower fuselage longerons at the tail post and weldments in the rudder hinge post area, for corrosion and cracks. 2. The inspection specified in paragraph (1) must be repeated at intervals not to exceed 100 hours' time in service or 12 months, whichever occurs first. 3. Before further flight, all corroded or cracked parts must be replaced with the same partnumber or with approved equivalent parts, or repaired in accordance with an approved repair procedure. 4. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection time in this Airworthiness Directive. Repairs and equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. Substantiating data for repairs and equivalent parts must be submitted by an owner or operator through an FAA Maintenance Inspector. This amendment is effective June 5, 1975.
84-12-02: 84-12-02 BELL HELICOPTER TEXTRON, INC: Amendment 39-4876. Applies to Bell Model 222 helicopters, certificated in all categories, that have nodal beam support fitting P/N 222-031-520-105 installed. (Airworthiness Docket 83-ASW-41.) Compliance is required as indicated, unless already accomplished. To prevent possible failure of the nodal beam left side aft support fitting, P/N 222-031- 520-105, accomplish the following: (a) For those aircraft that have support fitting P/N 222-031-520-105 installed with 1,100 or more hours time in service on the effective date of this AD, remove the fitting within the next 100 hours time in service. (b) For those aircraft that have support fitting P/N 222-031-520-105 with fewer than 1,100 hours time in service on the effective date of this AD, remove the fitting upon reaching 1,200 hours time in service. NOTE: Fitting P/N 222-031-520-105 may be replaced by a serviceable fitting of the same part number, or by P/N 222-031-592-103. (c) This AD establishes a 1,200 hour retirement life for all nodal beam left side aft support fittings P/N 222-031-520-105. (d) Any equivalent method of compliance with this AD must be approved by the Manager, Helicopter Certification Branch, Federal Aviation Administration, 4400 Blue Mound Road, Fort Worth, Texas 76106. (e) In accordance with Section 21.197, flight is permitted to a base where the actions required by this AD may be accomplished. NOTE: The following is provided as information only: Bell Helicopter Textron, Inc., Alert Service Bulletin 222-83-20 is the manufacturer's notification of the 1,200-hour life assignment to the nodal beam left side aft support fitting, P/N 222-031-520-105. Bell Helicopter Textron, Inc., Technical Bulletin 222-83-53 provides instructions for replacement of the P/N 222-031-520-105 aluminum fitting with a stainless steel fitting, P/N 222- 031-592-103, that has no retirement life. This amendment becomes effective July 11, 1984.
2005-14-02: The FAA is adopting a new airworthiness directive (AD) for all Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB-135 and Model EMB-145, -145ER, -145MR, -145LR, -145XR, -145MP, and -145EP airplanes. This AD requires inspecting to determine the part number of the left and right engine fire handles; and replacing the engine fire handles with engine fire handles having different part numbers if necessary. This AD is prompted by cases of the internal circuit of the engine fire handle failing. We are issuing this AD to prevent failure of the internal circuit of the engine fire handle that could disable the fuel shut-off valves and the discharge of the fire extinguishing agent, which, in the event of a fire, could result in the inability to extinguish a fire.
75-16-19: 75-16-19 FLUG-und FAHRZEUGWERKE A.G.: Amendment 39-2293. Applies to Diamant HBV gliders, all serial numbers, and Diamant 16.5 gliders, S/N 011 through 069, except 030, 031, 036, 058, 067, and 068, certificated in all categories. Compliance is required within 25 hours' time in service after the effective date of this AD, unless already accomplished. To prevent jamming of the rudder, accomplish the following: (a) Visually inspect and measure the fin fairing overlap of the rudder nose for right full rudder to assure an overlap of more than 0.4 inc. (10 mm) in accordance with Flug-und Fahrzeugwerke A.G. Service Bulletin No.2, dated May 15, 1970, or an FAA-approved equivalent. (b) If fin fairing overlap measured in accordance with paragraph (a) of this AD is less than 0.4 in. (10 mm), modify (lengthen) the rudder nose by bonding fiberglass strips to the nose in accordance with Flug-und Fahrzeugwerke A.G. Service Bulletin No.2, dated May 15, 1970, or an FAA-approvedequivalent. This amendment becomes effective August 12, 1975.
97-16-02: This amendment adopts a new airworthiness directive (AD) that is applicable to Robinson Helicopter Company (Robinson) Model R44 helicopters. This action requires inspections of the belt tension actuator switches (up-limit switches) for proper operation, and replacement if necessary; and replacement of a certain part-numbered clutch assembly. This amendment is prompted by six occurrences of prematurely worn sprag clutches. The actions specified in this AD are intended to prevent failure of the sprag clutch to lock in the driving direction, which would result in loss of power to the main rotor system and a subsequent forced landing; or failure of the sprag clutch to unlock in the overrunning direction, which, if combined with engine failure, would result in an inability to autorotate and a subsequent loss of control of the helicopter.