Results
47-21-07: 47-21-07 NAVION: (Was Mandatory Note of AD-782-3.) Applies to Serial Numbers NAV-4-10 Through 20, 22 Through 26, 28, 29, 31 Through 49, 51, 52, 55 Through 58, 60, 63, 73, 76, 79, 82 Through 84, 88 Through 95, 99 Through 104, 106, 108, 110, 112 Through 116, 120 Through 122, 124, 125, 130, 133, 141, 151, 153, 158, 163, 171. To be accomplished prior to August 1, 1947. Some airplanes were delivered with a cork or rubber filler strip cemented to the upper surface of the 145-42201-71 carburetor air intake scoop where the scoop fits over the flange of the air mixing chamber. This strip may becomes dislodged and drawn into the air induction system. To prevent this, replace the filler strip with a 3 1/8-inch x 5/8-inch dural strip of 0.093- inch thickness, flush-riveted to the scoop. (NAA Field Service Bulletin No. 15 covers this subject.)
47-25-07: 47-25-07 GLOBE: (Was Mandatory Note 11 of AD-766-5.) Applies to Models GC-1A and GC-1B Aircraft Serial Numbers 1001 to 1119 Inclusive. Compliance required prior to August 1, 1947. If an oil radiator is or has been installed, inspect the forward end of the engine's left oil galley outlet port and remove steel sleeve, Continental P/N 25206, if found to be installed. This is necessary to insure that positive lubrication is being provided the No. 6 cylinder connecting rod bearing. (Globe Customer Service Maintenance Bulletin No. 13 covers this same subject.)
2021-09-03: The FAA is correcting an airworthiness directive (AD) that was \npublished in the Federal Register. That AD applies to certain Airbus \nCanada Limited Partnership Model BD-500-1A10 and BD-500-1A11 airplanes. \nAs published, two references to a Transport Canada Civil Aviation \n(TCCA) AD number specified in the regulatory text are incorrect. This \ndocument corrects those errors. In all other respects, the original \ndocument remains the same.
2003-17-02: This amendment adopts a new airworthiness directive (AD) that applies to all EXTRA Flugzeugbau GmbH (EXTRA) Models EA-300/200, EA- 300L, and EA-300S airplanes. This AD requires you to inspect the fuel selector valve for leakage and the wing for structural damage and correct any damage or leakage. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct fuel leakage in the wings, which could lead to structural damage of the wings and possible reduced structural margins. Reduced structural margins could lead to eventual structural failure.
2016-08-19: We are adopting a new airworthiness directive (AD) for certain Mitsubishi Heavy Industries, Ltd. Models MU-2B-30, MU-2B-35, MU-2B-36, MU-2B-36A, and MU-2B-60 airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as reports of cracks found in the attach fittings of the main landing gear oleo strut. We are issuing this AD to require actions to address the unsafe condition on these products.
75-11-03: 75-11-03 SEMCO BALLOONS: Amendment 39-2200. Applies to Model T, Model TC-4A and Model Challenger balloons certificated in the Balloon category. Compliance required as indicated. Improper owner/operator assembly of the deflation system has resulted in excessive force being required to operate the deflation cable and fraying of the deflation cable end. The frayed cable end may draw deflation sleeve material into the hole in the locking block and brass rod preventing proper operation of the deflation system. To prevent these occurrences, accomplish the following: (a) Prior to each flight after the effective date of this AD, and until Revision 1, dated April 18, 1975, or later equivalent FAA approved revision to the Balloon Flight Manual is incorporated, accomplish the following check procedures. The pilot may perform these check procedures. 1. Check the portion of the end of the deflation cable which protrudes from the side of the aluminum locking block stamped "out" for fraying or loose strands with the hand or a cloth. If not smooth and free of loose strands, repair or replace before further flight. 2. During inflation, check the routing of the deflation cable. The deflation cable should lead from the basket through the fairlead ring sewn to the inside of the envelope, then in a straight line to the side of the locking block marked "in" and then to the outside of the envelope. The cable should not wrap around the locking block. If cable routing is not correct, reassemble the deflation system properly prior to flight. (b) Within 20 hours time in service after the effective date of this AD, obtain and incorporate Revision 1, dated April 18, 1975, or later equivalent FAA approved revision in the applicable Balloon Flight Manual. NOTE: Revision 1, dated April 18, 1975, to the applicable Balloon Flight Manual may be obtained on request to Semco Balloons, Route 3, Box 514, Griffin, Georgia 30223. The model of the balloonfor which the revision is desired should be specified, also the name and address to which it is desired that the revision be sent. These revisions are also available for examination in Room 274, FAA Building, 3400 Whipple Avenue, East Point, Georgia 30344. This amendment becomes effective May 19, 1975.
73-26-04: 73-26-04 MCDONNELL DOUGLAS: Amdt. 39-1760. Applies to Model DC-10-10, DC-10-30, and DC-10-30F airplanes certificated in all categories. \n\n\tCompliance required within the next 10 hours' of flight for Model DC-10-10 airplanes and 50 hours' of flight for Model DC-10-30 and DC-10-30F airplanes after the effective date of this AD, unless already accomplished. \n\n\tTo determine that the correct nose cowl attach bolts are installed and to assure the proper installation of the bolts, conduct a one-time inspection of the wing mounted engine nose cowl attach bolts and take corrective action in accordance with the following: \n\n\t(a)\tRemove bolts P/N 71658-6 (identified by 71658-6 stamped on the bolt head), if installed, and replace with P/N EWB 22-6-14 bolts, or FAA Western Region approved equivalent bolts (see paragraph (f)), in accordance with the instructions in paragraph (b). \n\n\t(b)\tInstall bolts P/N EWB 22-6-14, identified by HI PSI EWB 22-6 stamped on the bolt head, or FAA WesternRegion approved equivalent. Bolts must protrude through the nut by .030 to .180 inch. Bolts protruding more than .180 inch must have washers P/N MS 20002-6, P/N WPL 22-6, or FAA Western Region approved equivalent washers added between the existing countersunk washer P/N WCL22-6 and the nose cowl attach fitting to meet the .030 to .180 inch protrusion range. The grip length, -14, is not indicated on the bolt head and numbers stamped on the bolt head other than EWB 22-6 should be disregarded. \n\n\t(c)\tInspect all engine flange nutplates and replace any that are cracked or have attach rivets sheared off. As an alternative, accomplish either (1) or (2) below. \n\n\t\t(1)\tRemove the nut from the nutplate by bending the tangs of the retainer and install a new nut from nutplate General Electric (G.E.) P/N 9698M80P01 and rebend the nutplate tangs to secure the nut. \n\n\t\t(2)\tRemove the nutplate by chisel or grinding the rivets. Modify washer P/N MS20002-5 by drilling I.D. to .378/.388 inch. Reidentify the washer as G.E. P/N 9146M8-4P01 and install under nut G.E. P/N 9629-M48P06. \n\n\t(d)\tBack all bolts out until clampup torque is removed and make a running torque check of nut retention. Nuts with less than 10-inch-pounds of locking torque must be replaced, or accomplish either (1) or (2) below. \n\n\t\t(1)\tThoroughly clean the nose cowl and mating engine flange holes, bolts and nut threads with a brush and 1, 1, 1 Trichloroethane (MIL-T-81533), Naptha, or MEK (FED TT-M-261). Allow to dry completely after cleaning. Apply primer MIL-S-22473, Grade T, Form R, to bolt threads and allow to dry completely. Apply locking sealant MIL-S-22473, Grade A or Grade AV, or Loctite 271 on the first three bolt threads. These instructions are per Douglas Process Standard (DPS) 3.51, except that Loctite is an acceptable material not covered by the DPS. \n\n\t\t(2)\tAfter the bolts have been torqued in accordance with paragraph (e), below, clean the exposed threads and nut end per (d) (1), above, and puddle PR1422 class B sealant with accelerator to fill bolt end exposed threads. Cap bolt end with PR1422 sealant and extend the sealant partially over the nut (Reference DPS 2.50). \n\n\t(e)\tLubricate nuts, bolt threads, and washers with MIL-L-25681 per DPS 1.22, or with an FAA Western Region approved equivalent lubricant. If the (D) (1) procedure is used, lubricate bolt shank and washers under the bolt head only (no lubricant on the bolt or nut threads). Torque bolts to 28 to 32 foot pounds. Reference: McDonnell Douglas Maintenance Manual Chapter 71-11-00, page 206. \n\n\t(f)\tBolts P/N R21T5B1-6F14, P/N VS200-3F6-14, P/N EWB TM9-6-14, or P/N BAC B30MT6T14 are, for the purpose of complying with this AD, FAA Western Region approved equivalents for bolt P/N EWB 22-6-14. When bolt P/N BAC B30MT6T14 is installed, the bolt must protrude through the nut by .030 to .130 inch and have washers installed per paragraph (b) if the bolt protrudes more than .130 inch. \n\n\tNOTE: McDonnell Douglaswires C1-SVC-DC10COM-167, C1-SVC-DC10COM-168, C1-SVC-DC10COM-170, C1-SVC-DC10COM-176 cover the procedures described above. \n\n\t(g)\tSpecial flight permits may be issued under FARs 21.197 and 21.199 for the purpose of moving the aircraft to a base to accomplish maintenance to comply with this AD. \n\n\t(h)\tPrior to installation of any quick engine change (QEC) unit, verify accomplishment of this AD. \n\n\tThis amendment is effective December 19, 1973, for all persons except those to whom it was made effective immediately by telegram dated November 7, 1973.
2003-14-18: This amendment adopts a new airworthiness directive (AD) for the specified Sikorsky Aircraft Corporation (Sikorsky) model helicopters that requires removing non-conforming main landing gear brake discs (discs) and replacing them with different part-numbered airworthy discs. It also requires revising the Rotorcraft Flight Manual (RFM) to adjust takeoff and landing distances until the discs are replaced. This amendment is prompted by the manufacture of some discs using inferior materials. The actions specified by this AD are intended to prevent reduced braking performance and subsequent loss of control of the helicopter.
2024-22-02: The FAA is superseding Airworthiness Directive (AD) 2023-21- 02, which applied to certain Airbus SAS Model A330-200 series, A330-200 Freighter series, A330-300 series, A330-800 series, and A330-900 series airplanes. AD 2023-21-02 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. This AD was prompted by a determination that new or more restrictive airworthiness limitations are necessary. This AD continues to require certain actions in AD 2023- 21-02 and requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, 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.
2016-08-09: We are adopting a new airworthiness directive (AD) for certain Pratt & Whitney Division (PW) PW4000-94 inch and PW4000-100 inch model turbofan engines. This AD was prompted by a report of a crack found in the high-pressure compressor (HPC) 10th stage disk. This AD requires performing an ultrasonic inspection (USI) or an eddy current inspection (ECI) of the HPC 10th stage disk. We are issuing this AD to prevent failure of the HPC 10th stage disk, uncontained disk release, damage to the engine, and damage to the airplane.