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2002-04-08: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-600, -700, -700C, and -800 series airplanes, that requires a one-time inspection of certain fasteners in rudder pedal housings to determine if pan-head fasteners are installed, and replacement of existing fasteners with improved fasteners, if necessary. The actions specified by this AD are intended to prevent loss of free movement of the rudder pedals, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
89-07-17: 89-07-17 MCDONNELL DOUGLAS: Amendment 39-6169. \n\n\tApplicability: Model DC-9 series, Model DC-9-80 series, Model MD-88, and C-9 (military) series airplanes, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo detect center tank fuel pump failures, accomplish the following: \n\n\tA.\tWithin 10 calendar days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) to add the following, and provide to flight crews. This may be accomplished by inserting a copy of this AD in the AFM: \n\n\t\tSECTION I - LIMITATIONS \n\n\t\tFUEL MANAGEMENT \n\n\t\tAdd the following wording at the beginning of this section: "Prior to engine start on any flight where center tank fuel is present and will be needed for that route segment, the center tank fuel pumps must be individually checked to verify pump operation. This must be accomplished by observing that both inlet fuel pressure low lights extinguish when each individual center tank pump is activated. \n\n\t\tNOTE: Center tank pumps on aircraft with a center tank fuel pump low pressure warning system installed are not required to be checked in accordance with these procedures." \n\n\tB.\tAn 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, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\t\tNOTE: The request should be forwarded through an FAA Principal Operations Inspector (POI), who may add any comments and then send it to the Manager, Los Angeles Aircraft Certification Office. \n\n\tThis amendment (39-6169, AD 89-07-17) becomes effective on May 4, 1989.
2002-05-01: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200, 747-300, 747SP, and 747SR series airplanes powered by Pratt & Whitney JT9D-3 or JT9D-7 series engines. That AD currently requires inspections of the vertical chords of the aft torque bulkhead of the outboard nacelle struts, corrective action, if necessary, and a modification of the vertical chords, which ends the inspections. This amendment will reduce the compliance time and repetitive intervals for the currently required inspections. These actions are necessary to prevent cracking of the vertical chords adjacent to the lower spar fitting, which could result in separation of the diagonal brace load path. Continued operation with a separated diagonal brace load path increases loads on the upper link, midspar fitting, and dual side links, which could result in separation of the strut and engine from the airplane. These actions are intended to address the identified unsafe condition.
2020-03-20: The FAA is adopting a new airworthiness directive (AD) for certain The Boeing Company Model MD-11, MD-11F, and 717-200 airplanes, all Model 737-8 and 737-9 airplanes, all Model 737-600, -700, -700C, - 800, -900, and -900ER series airplanes, certain Model 747-400 and 747- 400F series airplanes, certain Model 757 and 767 airplanes, and all Model 777 airplanes. This AD requires revising the existing airplane flight manual (AFM) to include a limitation to prohibit operations that require less than 0.3 required navigational performance (RNP) within a specified area for airplanes having a certain multi-mode receiver (MMR) with certain software installed. This AD was prompted by reports of the loss of global positioning system (GPS) data or degraded GPS positional accuracy while using a certain MMR. The FAA is issuing this AD to address the unsafe condition on these products.
2015-17-17: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney (PW) PW4164-1D, PW4168-1D, PW4168A-1D and PW4170 engines, and certain PW4164, PW4168, and PW4168A turbofan engines. This AD was prompted by fuel nozzle-to-fuel supply manifold interface fuel leaks. This AD requires inspecting fuel nozzles for signs of leakage, replacing hardware as required, and torqueing to specified requirement. We are issuing this AD to prevent fuel leaks which could result in engine fire and damage to the airplane.
2015-17-16: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-600-2B19 (Regional Jet Series 100 & 440) 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.
89-11-04: 89-11-04 FOKKER: Amendment 39-6220. Applicability: Model F-28 series airplanes, Serial Numbers 11003 through 11241, 11991 and 11992, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent decompression of the aircraft during flight, accomplish the following: A. For airplanes in pre-Service Bulletin F28/21-16 configuration, within 30 days after the effective date of this AD, or upon the accumulation of 75,000 landings, whichever occurs later, inspect the frame 1600 center bracket for cracks, and repair, if necessary, in accordance with Fokker Service Bulletin F28/53-A92, Revision 1, dated July 15, 1988. Repeat this inspection at intervals not to exceed 4,500 landings. B. For airplanes in post-Service Bulletin F28/21-16 configuration, within 30 days after the effective date of this AD, or upon the accumulation of 50,000 landings, whichever occurs later, inspect the frame 1600 center bracket for cracks, andrepair, if necessary, in accordance with Fokker Service Bulletin F28/53-A92, Revision 1, dated July 15, 1988. Repeat this inspection at intervals not to exceed 3,000 landings. C. 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. D. 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 requirements of 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 Fokker Aircraft USA, Inc., 1199 N. Fairfax Street, Alexandria, Virginia 22314. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6220, AD 89-11-04) becomes effective on June 22, 1989.
87-09-02 R2: 87-09-02 R2 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-6399. Final copy of Priority Letter AD, as revised. Docket No. 87-ASW-17. Applicability: All BHTI Model 222 helicopters, certificated in any category, with drive hub assembly, part number (P/N) 222-010-417-009, installed. Compliance with paragraphs (a) and (b) is required immediately upon receipt of this AD, unless already accomplished. To prevent possible failure of the drive hub studs which could result in loss of flight control and subsequent loss of the helicopter, accomplish the following: (a) Remove nuts and washers from the studs which attach spline plate, P/N 222-310- 418-105/-107, to the drive hub assembly, P/N 222-010-417-009. (b) Visually inspect washers, P/N AN960-416, and mating surface on the spline plate, P/N 222-310-418-105/-107, for any signs of fretting, cracking, or wear. (1) If any fretting or wear is found, replace spline plate, P/N 222-310-418- 105/-107, and drivehub assembly, P/N 222-010-417-009. (2) If no fretting or wear is found, install new nuts, P/N MS21042L4, and washers, P/N AN960-416, and torque nuts to 100-pounds plus friction (tare) torque. (c) After completing requirements of paragraphs (a) and (b) and at intervals not to exceed 50 hours' time in service thereafter; apply 50 inch-pounds of torque to the spline plate, P/N 222-310-418-105/-107, retaining nuts. (1) If the nuts do not move, the nut torque is sufficient. (2) If one or more nuts move prior to reaching 50 inch-pounds, replace spline plate, P/N 222-310-418-105/-107, and drive hub assembly, P/N 222-010-417-009. (Maintenance manual 222-MM-1, Section 65-20-00, paragraphs 65-33 and 65-35 applies to this.) (d) An alternate method of compliance or adjustment of the compliance time, which provides an equivalent level of safety, may be used when approved by the Manager, Rotorcraft Certification Office, Rotorcraft Directorate, Aircraft Certification Office, FAA, Southwest Region, Fort Worth, Texas. (e) In accordance with FAR Sections 21.197 and 21.199, flight is permitted to a base where inspections required by this AD may be accomplished. This amendment (39-6399, AD 87-09-02 R2) becomes effective on December 22, 1989, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD's 87-09-02, issued April 24, 1987, and 87-09-02 R1, issued April 28, 1987, which contained this amendment.
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