Aircraft-logs.com

Results
2000-23-09: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires a one-time inspection to detect wear of the hydraulic pump hoses, and corrective action, if necessary. This AD also requires relocation of the clip that secures the left forward hold-open rod of both nacelles. The actions specified by this AD are intended to prevent chafing and consequent rupture of the hydraulic line and loss of hydraulic pressure, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
98-20-28: This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 airplanes. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
77-13-01: 77-13-01 GRUMMAN AMERICAN AVIATION CORPORATION (GAAC): Amendment 39-2919 as amended by Amendment 39-3003 is further amended by Amendment 39-3183. Applies to GAAC Model G-159, all serial numbers, and Model G-1159, serial numbers 1 through 208 and 775, airplanes certificated in all categories. Compliance required within 10 hours time in service after June 21, 1977, unless already accomplished. To prevent injury to an occupant of any jumpseat located between fuselage stations 119 and 169 on GAAC Models G-159 and G-1159 airplanes, accomplish one of the following: (a) Install a placard either on the bulkhead adjacent to the jumpseat or at any equivalent location approved by the Federal Aviation Administration utilizing a minimum of 3/16 inch high letters with the wording: "JUMPSEAT OCCUPANCY DURING TAXI, TAKEOFF, OR LANDING PROHIBITED." or (b) Modify in the following manner: 1. The Model G-159 nose landing gear drag strut fused or bulkhead modification in accordance with GAAC Aircraft Service Change No. 226, Part I or II, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. 2. The Model G-1159 nose landing gear wheel well bulkhead is modified to eliminate drag strut penetration in accordance with GAAC Aircraft Service Change No. 226, Part II, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, or (c) Upon a grant of extension of compliance time by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, the required placard may be removed for the length of the extension. Interested operators must furnish documentation with justification for the need for an extension to the Federal Aviation Administration, Chief, Engineering and Manufacturing Branch, P.O. Box 20636, Atlanta, Georgia 30320 by July 21, 1978. Also required in this documentation isevidence of a firm commitment from GAAC or a qualified modifier on the available date for the modification kit for that serial number aircraft. Each request for an extension will be handled on an individual aircraft basis. When either of the modifications described in paragraph b(1) or b(2) are accomplished, or the individual grant of extension is issued in accordance with paragraph (c), the required placard of paragraph (a) may be removed. However, grants of extension of compliance time will not be issued for any date beyond November 8, 1979. After November 8, any G-159 or G-1159 aircraft with a jumpseat installed between fuselage stations 119 and 169 must have installed either the modification in paragraph b(1) or b(2), or the placard in paragraph (a). Amendment 39-2919 became effective June 21, 1977. Amendment 39-3003 became effective August 8, 1977. This Amendment 39-3183 becomes effective April 21, 1978.
2013-06-02: We are adopting a new airworthiness directive (AD) for Diamond Aircraft Industries GmbH Models DA 42 M-NG and DA 42 NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the engine air inlet filter is subject to icing. We are issuing this AD to require actions to address the unsafe condition on these products.
98-20-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires repetitive detailed visual inspections of the windshield wiper assembly for discrepant conditions, and corrective actions, if necessary. 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 failure of the windshield wiper assembly, which could result in loss of visibility; or damage to the propeller(s), possible penetration of the fuselage skin, and consequent depressurization of the airplane.
72-20-01: 72-20-01 HAWKER SIDDELEY AVIATION LTD.: Amdt. 39-1523. Applies to Hawker Siddeley deHavilland Model DH-114 "Heron" airplanes. Compliance required as indicated. To prevent possible fatigue failure of the primary airplane structure accomplish the following: (A) Before the accumulation of the total hours' time in service specified in Column B for the applicable component specified in Column A, or within the next 100 hours' time in service after the effective date of this AD, whichever occurs later, and thereafter before the accumulation of the specified total hours' time in service on the replacement component, comply with the applicable paragraph of this AD specified in Column C: Column A Component Column B Service Life Column C AD Paragraph (1) Airframes 30,000 Hours (B) (2) Each component of an airframe not otherwise specified in this AD. 30,000 Hours (C) (3) Wing assemblies which do not incorporate modification 520, and fuselage center section lower spar booms, P/N 14FS2939 that do not incorporate modification 492. 3,500 Hours (D) (4) Wing assemblies that incorporate modification 520 and which have not been reworked in accordance with paragraph (e)(2). 15,000 Hours (E) (5) Wing assemblies which incorporate modification 520 that have been reworked in accordance with subparagraph (E)(2). 15,000 Hours' since reworked in accordance with subparagraph (E)(2) or 30,000 hours' total time in service whichever occurs first (E)(1) (6) Vertical fin front attachment fittings (R.H. and L.H.). 15,000 Hours (F) (7) Elevator trim tab connecting rods P/N 14TE.431A (R.H. and L.H. Elevator). 15,000 Hours (G) (B) Replace an airframe with an airframe of the same part number or a part number approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, that has accumulated less than 30,000 hours' time in service. (C) Replace each component of an airframe with a component of the same partnumber or a part number approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, that has accumulated less than 30,000 hours' time in service. (D) Comply with either of the following: (1) Replace the wing assembly with a wing assembly that has modification 520 incorporated and that has accumulated less than 15,000 hours' time in service, including the hours' time in service prior to the incorporation of Modification 520, and incorporate modification 492 on the wing carry-through structure in the fuselage center section in accordance with DeHavilland Aircraft Service Modification News Sheet, Modification No.: HERON 492, as amended through Amendment No. 3, dated March 6, 1956, or an FAA-approved equivalent. (2) Incorporate Modification 520 on the wing main spar lower boom in accordance with DeHavilland Aircraft Service Modification News Sheet, Modification No.: HERON 520, Issue 2, dated December 17, 1956, or an FAA-approved equivalent, and incorporate Modification 492 on the wing carry-through structure in the fuselage center section in accordance with DeHavilland Aircraft Service Modification News Sheet, Modification No.: HERON 492, as amended through Amendment No. 3, dated March 6, 1956, or an FAA-approved equivalent. (E) Comply with the following: (1) Replace the wing assembly with a Modification 520 Wing Assembly of the same part number that has accumulated less than 15,000 hours' time in service, including the hours' time in service prior to the incorporation of Modification 520, or (2) If the wing assembly has not accumulated 30,000 hours' time in service, including the hours' time in service prior to the incorporation of Modification 520, and the rework specified in this subparagraph has not been accomplished, rework the wing assembly as follows: (i) Rework the basic wing structure by incorporating modification 1585 in accordance with Hawker Siddeley Aviation Limited ModificationLeaflet "Civil Modification" for Modification No.: HERON 1585 with Amendment No. 4 incorporated, or an FAA-approved equivalent. (ii) Replace the existing flap datum hinge links with new links, P/N 14 WF.453 (L.H.) and P/N 14 WF.454(R.H.) or an FAA-approved equivalent, unless already accomplished within the last 4,000 hours' time in service; (iii) Replace the existing forward fork joint fittings (P/N 14 WF.1) and the forward eye joint fittings (P/N 14 WF.3), located between the inner and center flap sections with new fittings of the same part numbers in accordance with Hawker Siddeley Aviation Limited Repair Drawing RD. 14 WF.109, dated January 23, 1970, or an FAA-approved equivalent; (iv) Replace the small angle brackets located on the forward face of the rear vertical flange at wing rib No. 01 near the inner flap section inner hinge bracket attachment with new brackets, P/N 14 W.5621 and 14 W.5623 (Modification 1076, full version) or an FAA-approved equivalent.(v) Replace the engine mounting pickup straps, P/N 14-2W.555ND, and strap doublers, P/N 14 W.1715ND, with new straps and strap doublers of the same part numbers in accordance with paragraph 5.2 of Hawker Siddeley Aviation Limited, Technical News Sheet; Series: HERON (114) No. W.15, Issue 1, dated October 27, 1969, or an FAA- approved equivalent; and (vi) Replace the magnesium parts in the flap hinge assemblies with aluminum-copper alloy parts by incorporating modification 1098 in accordance with Hawker Siddeley Aviation Modification Leaflet "Civil Modification" for Modification No. HERON 1098, with Amendment No. 2 incorporated, or an FAA-approved equivalent. (F) Replace - (1) Vertical fin front attachment fittings with new fittings, P/N's 14.FS-4669 (left hand) and 14.FS-4670 (right hand), in accordance with DeHavilland Aircraft Service, Modification News Sheet No. HERON 869, dated December 12, 1956, or an FAA-approved equivalent, and (2) Vertical Channels,P/N's 14FS.187 (left hand) and 14FS.188 (right hand) on the aft face of the stub fin portion of Bulkhead 6 with new channels of the same part number in accordance with Hawker Siddeley Aviation Limited, Repair Drawing RD.14FS.293, dated February 10, 1972, or an FAA-approved equivalent. (G) Replace elevator trim tab connecting rods, P/N 14 TE.431A, and fork engs, P/N 4T.55 (two each per airplane), with new rods and fork ends of the same part number. (H) Operators who have not kept records of hours' time in service on any part to which a provision of the AD applies shall substitute airplane hours' time in service in lieu thereof. (Hawker Siddeley Aviation Limited, Technical News Sheet; Series: HERON (114) No. M.9, Issue 2, dated July 3, 1972, covers this same subject.) This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the airmail letter dated July 27, 1972 which contained this amendment.
58-10-09: 58-10-09 VICKERS: Applies to all Viscount 700 Series Aircraft Equipped With 14-Inch Stroke Landing Gear Oleos. Compliance required as indicated. On aircraft equipped with 14-inch stroke oleos, cases of circumferential cracks have occurred in the main oleo cylinder, P/N 74450-3. The cracks were at the radius, where the cylinder intersects with the 30-degree taper and 2-3/8 inches above the torsion link lugs, either side of the fore and aft center line. Vickers-Armstrongs has issued the following corrective measures which the British Air Registration Board considers mandatory: 1. On aircraft which have reached a total of 1,000 flying hours and each subsequent 200 landings, the oleos should be visually inspected for cracks around the cylinder circumference. If cracks are suspected, the area should be checked with dye penetrant or approved equivalent. 2. Where cracks are confirmed, the part is considered serviceable subject to a daily visual inspection, providing the combined total length of cracks does not exceed 3 inches and individual cracks do not exceed 1-1/2 inches each in length. 3. Where combined total length of cracks exceeds 3 inches but is not greater than 5 inches, and length of individual cracks not greater than 2-1/2 inches, cracks must be blended out before next flight and area reprotected with seaplane varnish or approved equivalent. Maximum depth of blending or crack must not exceed 0.050 inch. The part is then considered serviceable subject to a check by dye penetrant or approved equivalent every 135 hours. 4. If the length of depth of the cracks exceed the limits quoted in item 3, the part is no longer considered serviceable and must be replaced with new cylinder, in accordance with Vickers Mod. No. D.2694. 5. After embodiment of the new cylinders to either Part (a) or (c) of Mod. D.2694, the above inspections may be discontinued. 6. If no cracks are found during the initial inspection and the cylinderis shotpeened in accordance with PTL 191, Issue 3, the cylinder may be reinspected using dye penetrant or approved equivalent every 1,000 landings. 7. Cylinders having a total length of cracks exceeding 3 inches but not greater than 5 inches, with the length of individual cracks not greater than 2-1/2 inches and the depth of cracks not exceeding 0.050 inch, which have been reworked as follows may be reinspected using dye penetrant or FAA approved equivalent every 500 landings. Rework consists of: (a) Blend out the crack using a radius of blending not less than 0.5 inch with the maximum depth of blending not to exceed 0.050 inch. (b) Shotpeen the cylinder in accordance with PTL 191, Issue 3. (c) Reprotect the reworked area with seaplane varnish or FAA approved equivalent. The FAA concurs with this action and considers compliance therewith mandatory. (Vickers-Armstrongs PTL No. 191, Issues 2 and 3, and Modification D.2694 cover this subject.) This supersedes AD 58-07-05.
63-07-04: 63-07-04 ROLLS-ROYCE: Amdt. 549 Part 507 Federal Register April 2, 1963. Applies to All Model Dart Engines. Compliance required as indicated. To prevent failures in service of combustion chamber air casings of Pre-Modification 553 standard, which failures have been attributed to fatigue cracks originating around suspension pin soleplates, accomplish the following: (a) Within the next 100 hours' time in service after the effective date of this AD, on engines with combustion chamber air casings not incorporating Modification 553 standards except engines with air casings of Pre-Modification 97 standards, accomplish (1) or (2): (1) Install strengthened air casing incorporating Rolls-Royce Modification 553 standards; or (2) Install air casing straps using: (i) Mod. 612 standards which modification sets forth a positive location for antitear straps for Pre-Mod 553 air casings; or (ii) Mod. 1021 standards which modification covers Pre-Mod. 553 air casings which have been modified to Mod. 855 standards providing an additional boss for burner cleaning. (b) Remove air casings of Pre-Mod. 97 standard at the next engine overhaul and replace with air casings conforming to the standards set forth in (a). (Rolls-Royce Notice to Operators Dart Engines No. 99 Issue 3 dated June 29, 1962, covers the same subject.) This directive effective May 2, 1963.
2013-05-02: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes. This AD was prompted by reports of cracks of the hinge bearing lugs of the center section ribs of the horizontal stabilizer. This AD requires repetitive high frequency eddy current (HFEC) inspections for cracking of the left and right rib hinge bearing lugs of the aft face of the center section of the horizontal stabilizer; measuring crack length and blending out cracks; and replacing the horizontal stabilizer center section rib, if necessary. We are issuing this AD to detect and correct cracking in the hinge bearing lugs of the horizontal stabilizer center section ribs, which could result in failure of the lugs, and consequent inability of the horizontal stabilizer to sustain the required limit loads and loss of control of the airplane.
98-19-21: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 800 series turbofan engines. This action requires initial and repetitive ultrasonic inspections of fan blade roots for cracks, and replacement, if necessary, with serviceable parts. This amendment is prompted by reports of multiple fan blade root cracks in several factory test engines. The actions specified in this AD are intended to prevent fan blade failure, which could result in multiple fan blade release, uncontained engine failure, and possible damage to the aircraft. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of October 7, 1998. Comments for inclusion in the Rules Docket must be received on or before November 23, 1998.