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2006-04-09: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model CL-600-2C10 (Regional Jet Series 700, 701, & 702), CL-600-2D15 (Regional Jet Series 705), and CL-600-2D24 (Regional Jet Series 900) airplanes. This AD requires replacing the Camloc fasteners on the sidewall of the center pedestal. This AD results from reports of the Camloc fasteners on the sidewall of the center pedestal disengaging and interfering with an inboard rudder pedal. We are issuing this AD to prevent these fasteners from disengaging and interfering with an inboard rudder pedal, which could reduce directional controllability of the airplane.
92-20-05: 92-20-05 FOKKER: Amendment 39-8379. Docket No. 92-NM-68-AD. Applicability: Model F28 Mark 0100 series airplanes; serial numbers 11244 through 11256, inclusive; 11259; 11260; and 11268 through 11278, inclusive; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the wings, accomplish the following: (a) Prior to the accumulation of 18,000 landings or within 60 days after the effective date of this AD, whichever occurs later, replace the currently installed aluminum alloy rivets at the rib-to- auxiliary-spar attachment at wing station 10110 with nickel copper alloy rivets and Hilok bolts, in accordance with Fokker Service Bulletin SBF100-57-017, dated September 12, 1991. (b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch. (c) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The replacement shall be done in accordance with Fokker Service Bulletin SBF100-57- 017, dated September 12, 1991. 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 Fokker Aircraft USA, Inc., 1199 North Fairfax Street, Alexandria, Virginia 22314. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 17, 1992.
67-10-03: 67-10-03 DOWTY-ROTOL PROPELLERS: Amendment 39-570. Applies to Dowty- Rotol Propellers, (c) R.186/4-30-4/16 installed on Armstrong Whitworth Argosy AW-650; (c) R.175/4-30-4/13E installed on Fairchild F-27 and F-27B; (c) R.130/4-20-4/12E installed on Viscount 745D; and (c) R.148/4-20-4/21E installed on Viscount 744. Amendment 39-382 (32 F.R. 5366), AD 67-10-03, amended by Amendment 39-392 (32 F.R. 5464) is further amended by: Compliance required as indicated, unless already accomplished. To prevent failure of the propeller cylinders, P/N's RA.38581, RA.38581/1, RA.44133, RA.44133/1, RA.44709 and RA.62807, due to cracks, accomplish the following: (a) (1) For (c) R.148/4-20-4/21E propellers with 12,000 or more landings, within the next 10 landings (unless already accomplished within the last 70 landings), and thereafter at intervals not to exceed 80 landings since the last inspection, comply with (b). (2) For (c) R.186/4-30-4/16, (c) R.175/4-30-4/13E, and (c)R.130/4-20- 4/12E propellers with 12,000 or more landings, within the next 10 landings (unless already accomplished within the last 30 landings), and thereafter at intervals not to exceed 40 landings since the last inspection, comply with (b). (3) For propellers with 5,900 or more landings but less than 12,000, within the next 100 landings, unless already accomplished within the last 200 landings and thereafter at intervals not to exceed 300 landings since the last inspection, comply with (b). (4) For propellers with less than 5,900 landings, before accumulating 6,000 landings, and thereafter at intervals not to exceed 300 landings since the last inspection, comply with (b). (b) Inspect the propeller cylinder retaining nut threads for cracks in accordance with Dowty-Rotol Service Bulletin No. 61-521, Revision 3, dated November 1967, or later ARB- approved revision, using ultrasonic techniques or an equivalent approved by the Chief, Aircraft Certification Staff FAA European Region. (c) Notwithstanding (a), the repetitive inspection intervals required in (a)(3) and (4) are raised to 600 landings for (c)R.148/4-20-4/21E propellers. (d) If cracks are found, replace the propeller cylinder before further flight. (e) For the purposes of determining the total number of landings at which initial compliance with this AD is required, subject to acceptance by the assigned FAA maintenance inspector, the number of landings may be determined by dividing the propeller's hours of time in service by the operator's fleet average time from takeoff to landing for the airplane type. (f) Cylinders for which number of landings cannot be established must be classed as having above 12,000 landings. This amendment becomes effective April 1, 1968.
57-03-01: 57-03-01 CONVAIR: Applies to All 240 Series Aircraft. Compliance required at 12,000 hours of operation and as indicated below. As a result of several reports concerning cracks in the main outboard landing gear fitting, the following inspection should be conducted on all Model 240 Series aircraft: 1. Inspect P/N 240-1650716 for cracks running fore and aft on the inboard and outboard face of the fitting, above the fitting boss at the point of tangency of the boss and plate. This inspection must be made at each 1,000 hours of operation following the initial inspection at 12,000 hours. 2. Parts which have cracks not exceeding 2 inches in length may remain in service when properly stop-drilled with a 0.25-inch drill, and inspected daily for further crack progression or other damage. 3. Parts with cracks exceeding 2 inches in length must be replaced with an acceptable part. When replaced with a new part the above inspections are not required until the replacementpart has 12,000 hours of operation, at which time the above inspection procedure, item 1, is again in effect.
91-08-11: 91-08-11 BRITISH AEROSPACE: Amendment 39-6966; Docket No. 90-NM-237-AD. Applicability: Model BAe 146-200A series airplanes; Serial Numbers E2022 through E2025, E2028, E2030, E2031, E2034, E2036, and E2039 through E2048; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent reduced structural integrity of the fuselage pressure vessel, accomplish the following: A. For airplanes Serial Numbers E2022 through E2025, E2028, E2030, E2031, E2034, E2036, E2039 through E2048: Accomplish the following: 1. Within 30 days after the effective date of this AD, perform the following inspections: a. A detailed visual inspection (including the use of a dial test indicator and 10X magnifying glass, where appropriate) of the rivets in the polished fuselage skins and the polished fuselage skins to detect rivet abrasion damage, loose or missing rivets, and skin cracks, in accordance with paragraphs 2.A. and 2.B. of the Accomplishment Instructions of British Aerospace Service Bulletin 53-87, dated January 19, 1990. b. An ultrasonic inspection of the fuselage skin, to detect reduced skin thickness, in accordance with paragraphs 2.A. and 2.B. of the Accomplishment Instructions of British Aerospace Service Bulletin 53-87, dated January 19, 1990. 2. Repeat the inspections required by paragraph A.1. of this AD at intervals not to exceed 1,500 flights, as follows: a. For fuselage sections of the airplane that continue to be polished, perform visual and ultrasonic inspections on alternate halves of the fuselage (e.g., left and then right, etc.), in accordance with paragraphs 2.A. and 2.B. of the Accomplishment Instructions of British Aerospace Service Bulletin 53-87, dated January 19, 1990. b. For fuselage sections that have had the fuselage skin painted subsequent to findings of rivet or skin damage resulting from polishing, perform only a visual inspection of those areas for skin cracks and loose or missing rivets. c. For fuselage sections that have had the fuselage skin painted subsequent to findings of no rivet or skin damage resulting from polishing, no further action is required. 3. As a result of the inspections required by paragraph A.1. of this AD, accomplish the following: a. If skin cracks or loose or failed rivets are found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. b. Any rivets identified as category "A1" (between 0.002 to 0.000 inch in head height), must be replaced prior to further flight, with new rivets having the same part number, in accordance with paragraphs 2.A. and 2.B. of the Accomplishment Instructions of British Aerospace Service Bulletin 53-87, dated January 19, 1990. c. At intervals not to exceed 1,500 flights, apply protective treatment to all rivets identified as having curvededges, in accordance with paragraph 2.A.9. of British Aerospace Service Bulletin 53-87, dated January 19, 1990. B. For airplanes Serial Numbers E2022 through E2025, E2028, E2030, E2031, E2034, E2036, E2039 through E2048: Accomplish the following, in accordance with Paragraph 2.A. of British Aerospace Service Bulletin 53-98, dated September 26, 1990: 1. Within 6 months after the effective date of this AD, perform the following inspections: a. A detailed visual inspection of the designated areas of the fuselage skins for signs of corrosion. b. For airplanes that have been repainted, inspect the paint finish in the designated areas for underlying corrosion. 2. Repeat the inspections required by paragraph B.1. of this AD at intervals not to exceed 2,000 landings. 3. As a result of the inspections required by paragraph B.1. of this AD, accomplish the following: a. If the paint finish in any area shows bubbling or other signs of distress, prior to further flight, the paint must be removed in accordance with Chapter 20-10-10 of the Airplane Maintenance Manual to allow a more detailed visual inspection to determine the extent of the damage. b. If corrosion is found, prior to further flight, repair in a manner approved by the Manager, Standardization Branch, ANM-113, Transport Airplane Directorate. C. For airplanes Serial Numbers E2022, E2024, E2025, E2028, E2036, and E2045: Accomplish the following, in accordance with British Aerospace Service Bulletin 53-88, dated January 19, 1990: 1. Prior to the accumulation of the number of flights identified in the "Compliance Period from Initial Polishing" column in paragraph D.1. of the service bulletin, perform a close visual inspection of the designated areas of the polished fuselage skin. 2. Repeat the inspections required by paragraph C.1. of this AD at intervals not to exceed 1,500 flights. 3. As a result of the inspections required by paragraph C.1. of this AD, accomplish the following: a. If skin cracks or defects (loose or missing rivets) are found, prior to further flight, accomplish the following: (1) Record the findings of cracks or defects, in accordance with paragraph 2.A.(3) of the service bulletin. (2) If any loose rivets are found, remove the loose rivets and perform a detailed visual inspection to detect cracks around all vacant rivet holes using a 10X magnifying glass, in accordance with paragraph 2.A.(5) of the service bulletin. (3) Repair cracks in a manner approved by the Manager, Standardization Branch, ANM-113, FAA Transport Airplane Directorate. (4) Replace any missing or removed rivets with new rivets having the same part number. b. If no cracks or defects are found, no further action is necessary for this inspection cycle. D. Within 14 days after the inspections required by this AD, submit a report of all findings of the inspections, positive or negative, including charts, to British Aerospace, in accordance with Paragraph 2.A.(13) of British Aerospace Service Bulletin 53-87, dated January 19, 1990; Paragraph 2.A.(7) of Service Bulletin 53-88, dated January 19, 1990; and Paragraph 2.A.(4) of Service Bulletin 53-98, dated September 26, 1990. E. An alternative method 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, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. F. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041-0414. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington. This amendment (39-6966, AD 91-08-11) becomes effective on May 17, 1991.
2021-06-03: The FAA is adopting a new airworthiness directive (AD) for all The Boeing Company Model 777F series airplanes. This AD was prompted by a report of a water supply line that detached at a certain joint located above an electronic equipment (EE) cooling filter, leading to water intrusion into the forward EE bay. This AD requires deactivating the potable water system. The FAA is issuing this AD to address the unsafe condition on these products.
99-21-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 (Regional Jet Series 100) series airplanes, that requires a one-time inspection to detect damage of the input connectors and wiring of the main and auxiliary power unit (APU) battery chargers, and corrective action, if necessary. This amendment also requires installation of secure connectors for the battery charger input connections. In addition, this amendment requires, for certain airplanes, either the installation of a resistor in the battery charger wiring, or the installation of new batteries with internal resistors. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent increased risk of a short circuit and consequent electrical smoke or fire in the aft fuselage.
85-26-05: 85-26-05 GULFSTREAM AEROSPACE: Amendment 39-5203. Applies to Model GA-7 (Cougar) airplanes, all serial numbers, certified in any category. COMPLIANCE: Required within 50 hours time-in-service after the effective date of this AD unless previously accomplished. To prevent failure of the rudder torque tube, accomplish Paragraphs (a), (b) and (c) of the following AD in accordance with Gulfstream Aerospace Corporation (GAC) Service Bulletin (S/B) No. ME-21, dated November 1, 1985: (a) Visually inspect the rudder torque tube for corrosion or cracks. (b) If any cracks or excessive corrosion is found, prior to further flight replace the rudder torque tube, P/N 7CS10500-11. (c) If no cracks are found and no corrosion or only light surface corrosion exists on the rudder torque tube, prior to further flight apply corrosion protection treatment to the torque tube. (d) Aircraft may be flown in accordance with Federal Aviation Regulation 21.197 to a location wherethis AD can be accomplished. (e) An equivalent method of compliance with this AD, if used, must be approved by the Manager, Atlanta Aircraft Certification Office, 1075 Inner Loop Road, College Park, Georgia 30337; telephone (404) 763-7428. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Gulfstream Aerospace Corporation, P.0. Box 2206, Savannah, Georgia 31402- 2206, or the FAA, Rules Docket, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on January 3, 1986.
59-06-03: 59-06-03 MOONEY: Applies to Models M-20 and M-20A Serial Numbers 1002 Through 1364. Compliance required as indicated. A failure of a rudder hinge bearing bracket (P/N 4003) has occurred on a Mooney M- 20A. To preclude the possibility of similar failures occurring on these brackets or on the aileron and elevator hinge bearing brackets, the following inspection and rework is required as indicated: Within the next five flight hours, inspect the welds which attach the hinge bearing housing (7/8 inch O.D. x .058 inch 4130 steel tube) to the fixed surface hinge bearing channel (P/N 4002). Bearing bracket assemblies (P/N 4003) are installed as aileron, elevator, and rudder hinges. The inspection shall be conducted as follows: Remove paint from welds and, using a 10-power glass, inspect for cracks or inadequate weld (i.e. weld which does not completely fill fillet cross section area.) If cracks are found, the bearing brackets on that surface must be removed and a set of modified hinge bearing brackets (P/N 4003) installed prior to further flight. If inadequate welds are found (i.e., such as but not limited to, not completely, filling in between the face of the outer race and the top of the channel leg and/or inadequate fillet radius between the edge of the outer race and the top of the channel leg) the defective bearing brackets must be removed and a set of modified hinge bearing brackets (P/N 4003) installed on that surface not later than April 15, 1959. A set of hinge bearing brackets is defined as follows: Aileron --all three (3) hinge bearing brackets; elevator - outer two (2) hinge bearing brackets; rudder - upper two (2) hinge bearing brackets. The installation shall be accomplished as follows: (1) Install AN 960-3 washers (2) with each new hinge bearing bracket, one at each attach bolt between bracket and structure except at the tip elevator hinge where P/N 8389 shim should be used in place of the inboard washer. (2) Rudder (a) Remove fabric covering small "D" shaped cutout in plywood at trailing edge on right-hand side at each of the upper hinges. Do not remove gap tape or lower hinge bolt. (b) Replace hinge bearing bracket (2) and recover access openings with fabric patch (use Butyrate dope.) (3) Elevator (a) Remove fabric covering small "D" shaped cutout in plywood at trailing edge on under side at each of the outboard hinges. Do not remove gap tape or inboard hinge bolt. (b) Replace hinge bearing bracket (2) (see item (1) for use of ship at tip hinge bracket) and recover access opening with fabric patch (use Butyrate dope). (4) Aileron (a) Remove counterbalance weight fairing and two access plates at trailing edge of wing. (b) Disconnect control tube and remove aileron. (c) Check clearance between aileron gap strip and existing hinge bearing bracket. If this clearance is not approximately 1/16-inch, the gap strip may have to be dimpled at the hinge to allow clearance for heavier replacement bracket. (d) Replace hinge bearing bracket (3). (Mooney Aircraft Inc. Service Letters 20-44 and 20-45 cover this same subject.)
2021-04-14: The FAA is adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and A350-1041 airplanes. This AD was prompted by reports that suitable corrosion protection treatment had not been applied to certain areas of the seat track. This AD requires a one-time detailed inspection of the seat tracks between certain frames for suitable corrosion protection or presence of corrosion, and on- condition actions if necessary, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.