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2015-17-15: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2C10 (Regional Jet Series 700, 701, & 702) airplanes, Model CL-600-2D15 (Regional Jet Series 705) airplanes, Model CL-600-2D24 (Regional Jet Series 900) airplanes, and Model CL- 600-2E25 (Regional Jet Series 1000) airplanes. This AD was prompted by results of a design review indicating that the burst pressure of the flexible hose, used to vent oxygen from the high-pressure relief valve of the oxygen cylinder overboard, was lower than the opening pressure of the high-pressure relief valve, which could cause the flexible hose to burst before it can vent the excess oxygen overboard. This AD requires replacing the oxygen hose assembly with a new, improved assembly. We are issuing this AD to prevent the accumulation of oxygen in an enclosed space, which could result in an uncontrolled oxygen-fed fire if an ignition source is nearby.
86-15-07: 86-15-07 CESSNA: Amendment 39-5358. Applies to the following Models and Serial Numbers of airplanes certificated in any category which have been modified by the installation of an engine larger in size and/or horsepower than the Continental 0-200-A: \n\n\nMODELS\nSERIAL NUMBERS \n150\n17001 thru 17999, 59001 thru 59018 \n150A\n15059019 thru 15059350 \n150B\n15059351 thru 15059700 \n150C\n15059701 thru 15060087 \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo assure operation of the airplane within the approved center of gravity (cg) limits, accomplish the following: \n\n\t(a)\tWithin the next 25 hours time-in-service (TIS) after the effective date of this AD, accomplish the following: \n\n\t\t(1)\tWeigh the airplane to determine the empty weight (W1) and calculate the cg (cg1). The airplane, as weighed, must include full oil and unusable fuel (21 lbs at fuselage station 40.0 for standard fuel tanks). \n\n\t\t(2)\tAdd pilot weight (170 lbs at fuselage station39.0) to the empty weight (W1+170=W2) and calculate the cg (cg2) for this condition. If this cg is forward of fuselage station 32.2, add ballast between fuselage stations 70.69 and 76.44. (This was the location of the battery prior to the engine modification.) \n\n\t\t(3)\tDetermine the amount of ballast (B) required from the following equation: \n\t\t\t(D) x (W2) \n\t\t\tB = _________ ; where, \n\t\t\t\tX \n\t\t\tB = weight in pounds of ballast required by this AD. \n\t\t\tD = distance in inches the empty A/C (with pilot) cg must be moved aft in order to comply with this AD (D=32.2-cg2). Obtain cg2 from paragraph (2) above. \n\t\t\tW2 = empty weight in pounds of the airplane plus pilot determined in paragraph (2) above. \n\t\t\tX = distance in inches from the point where the ballast is installed to the required location of the new cg (fuselage station 32.2 in this case). Using the battery box location, X = 41.36. \n\n\t\t(4)\tFabricate the channel detailed in Figure 1. Mount the channel between fuselage stations 70.69 and 76.44 using the existing 041328-3 brackets. Attach with MS20470- AD4 rivets through the existing holes in brackets. Install the ballast in accordance with Figure 1. If ballast exceeds 60 pounds, contact the Wichita Aircraft Certification Office at the address given in paragraph (d) below for assistance. \n\n\t\t(5)\tIf the empty weight, as calculated in (1) above, plus the ballast exceeds 1142 lbs, prior to further flight, fabricate and install on the instrument panel a placard with a minimum letter size of 1/8 inch which states, "WARNING: THIS AIRPLANE LIMITED TO SINGLE OCCUPANT". If the empty weight exceeds 1195 lbs., equipment must be removed in order that this weight is not exceeded. The 1142 lbs and 1195 lbs are weight limitations established by Civil Air Regulations 3.74(b) (1) and 3.74(b) (2), respectively. \n\n\t(b)\tAirplanes which were weighed at the time of installation of the larger engine and have an empty weight cg (including pilot, oil and unusable fuel) aft of fuselage station 32.2 are exempt from paragraphs (a)(1), (a)(2), (a)(3) and (a)(4) of this AD. \n\n\t(c)\tAirplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. \n\n\t(d)\tAn equivalent method of compliance with this AD may be used if approved by the Manager, Wichita Aircraft Certification Office, FAA, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. \n\n\tThis amendment, 39-5358, becomes effective July 24, 1986. \n\n\nMATERIAL:\n2024-T3\nTHICKNESS:\n.040\nBEND RADII:\n.125\nSCALE:\n1/2\nDIMENSIONS:\nInches\n\nNOTE: Lead ballast can be stacked sheet stock, ingot, or bar stock. Attach sheet stock with a minimum of 4-AN4 bolts or equivalent. Attach ingots or bar stock with a minimum of 2- AN4 bolts or equivalent per piece of lead, install a large diameter washer, such as an AN 970-4 under both the bolt head and nut. Use either a locknut or a castellated nut with cotter pin\n\n\n\n\nCHANNEL\n\n\t\t\t\t\tFIGURE 1 -86-15-07
2002-03-15: This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and -300 series airplanes, that requires testing of the left- and right-hand potentiometer levers of the aileron flight control system, and follow-on or corrective action, as applicable. This amendment is necessary to prevent detachment of an aileron potentiometer lever, which could result in jamming of the elevator and/or aileron flight control systems and consequent reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
69-24-01: 69-24-01 AER PEGASO C.A.R.M.A.M.: Amdt. 39-877. Applies to Aer-Pegaso Model M.100S and C.A.R.M.A.M. Model M.200 gliders. Compliance is required within the next 25 hours' time in service after the effective date of this AD, unless already accomplished. To detect improper installation of the horizontal stabilizer to the glider, accomplish the following: (a) Install an inspection window on the left side of the dorsal fin to allow visual confirmation of the elevator "quick disconnect" attachment and paint the two plates of the elevator control transmission fork in accordance with Aer-Pegaso Technical Bulletin N.10/M- 100S, dated September 26, 1969, or an FAA-approved equivalent. (b) Install the following placard in the cockpit in clear view of the pilot: "Before the first flight after rigging the tailplane to the fuselage, look through the inspection window located on the left side of the dorsal fin and visually confirm that the end (ball bearing) of the elevator control lever is correctly engaged in the corresponding fork of the elevator control transmission. To do this, it may be necessary to move the control stick in the longitudinal direction in order to bring the lever end into view through the window. If the rigging is correct, the ball bearing will appear between the fork sides." This amendment becomes effective November 23, 1969.
2002-03-16: This amendment supersedes an existing airworthiness directive (AD) for Model OH-13E, OH-13H, and OH-13S helicopters manufactured by Bell Helicopter Textron, Inc. (BHTI). That AD currently requires either recurring liquid penetrant or eddy current inspections of the main rotor blade grip (grip) threads for a crack. If a crack is detected, that AD requires, before further flight, replacing the cracked grip with an airworthy grip. That AD also establishes a retirement life of 1200 hours time-in-service (TIS) for each grip. This amendment adds two part numbers (P/N) to the applicability and requires only recurring eddy current inspections of the grip threads. This AD also requires reporting any results of the grip inspections to the FAA Rotorcraft Certification Office. This amendment is prompted by the issuance of an AD for the civil BHTI Model 47 helicopters and the results of an accident investigation, an operator survey conducted by a trade association, various comments concerning the subject of the current AD, and a further analysis of field service data related to the BHTI Model 47 helicopters. The actions specified by this AD are intended to prevent failure of a grip, loss of a main rotor blade, and subsequent loss of control of the helicopter.
86-20-10: 86-20-10 ROLLS-ROYCE plc: Amendment 39-5415. Applies to Rolls-Royce Dart Mks., 506, 506F, 510, 510A, 511, 511-7E, 514, 514-7, and 515 turboprop engines. Compliance is required as indicated, unless already accomplished. To prevent cracking of high pressure turbine disks, install new or reworked oversize high pressure nozzle guide vane(s) in accordance with Rolls-Royce Dart (R-R) Service Bulletin (SB) Da72-451, Revision 5, dated June 1982, or FAA approved equivalent, by October 1, 1987. 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. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 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, Engine Certification Office, New England Region, may adjust the compliance time specified in this AD. R-R SB Da72-451, Revision 5, dated June 1982, identified and described in this document, is 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 this document from the manufacturer may obtain copies upon request to Rolls-Royce plc - East Kilbride, Attn: Dart Engine Service Manager, Glasgow G74-4PY, Scotland. This document may also be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Room 311, Rules Docket Number 86-ANE-19, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. This amendment becomes effective on November 4, 1986.
2003-15-04: This amendment adopts a new airworthiness directive (AD), applicable to all BAE Systems (Operations) Limited (Jetstream) Model 4101 airplanes, that requires inspection of the drive trunnion pins for the main landing gear (MLG) doors to determine the part number of the pins and corrective action if necessary. The actions specified by this AD are intended to prevent failure of the MLG and consequent reduced controllability of the airplane during takeoff or landing.
2002-03-08: This amendment supersedes an existing airworthiness directive (AD), that is applicable to Pratt & Whitney PW4000 series turbofan engines. That AD currently requires revisions to the Time Limits Section of the manufacturer's Engine Manuals (EM's) to include required enhanced inspection of selected critical life-limited parts at each piece-part exposure. This amendment modifies the airworthiness limitations section of the manufacturer's manual and an air carrier's approved continuous airworthiness maintenance program to incorporate additional inspection requirements. An FAA study of in-service events involving uncontained failures of critical rotating engine parts has indicated the need for mandatory inspections. The mandatory inspections are needed to identify those critical rotating parts with conditions, which if allowed to continue in service, could result in uncontained failures. The actions specified by this AD are intended to prevent critical life-limited rotating enginepart failure, which could result in an uncontained engine failure and damage to the airplane.
2015-17-08: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD was prompted by an in-service report of an uncommanded and unannunciated nose wheel steering during airplane pushback from the gate. This AD requires installing new cable assemblies with a pull-down resistor. We are issuing this AD to prevent an uncommanded nose wheel steering during takeoff or landing in the event of an open circuit in the steering system, and possible consequent runway excursion.
85-25-11: 85-25-11 CESSNA: Amendment 39-5234. Applies to Models 425 (Serial Numbers 425-0002 thru 425-0236) and 441 (Serial Numbers 441-0001 thru 441-0354) airplanes certificated in any category. Compliance: Required within the next ten hours time-in-service, unless previously accomplished. To preclude failure of the horizontal stabilizer front spar attachments accomplish the following: (a) Replace left and right horizontal stabilizer front spar attach bolt retaining nuts (Part Number NAS1291-8) in accordance with the instructions contained in Cessna Service Bulletin No. CQB85-25, Revision 1, dated December 16, 1985. Purchase replacement NAS1291-8 nuts exclusively from the Cessna Supply Division after November 22, 1985, per the above Cessna Service Bulletin. (b) Return removed NAS1291-8 nuts to Cessna in accordance with Cessna Service Bulletin No. CQB85-25, Revision 1, dated December 16, 1985. (c) Aircraft may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (d) An equivalent method of compliance with this AD may be used when approved by the Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, Central Region, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. All persons affected by this directive may obtain copies of the document referred to herein upon request to the Cessna Aircraft Company, Customer Services, Post Office Box 1521, Wichita, Kansas 67201 or the FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective February 12, 1986, as to all persons except those persons to whom it was made immediately effective by priority letter AD 85-25-11, issued December 18, 1985, which contained this amendment.