Results
75-08-01: 75-08-01 CANADAIR: Amendment 39-2150. Applies to all CL-44D4 and CL-44J airplanes. Compliance required as indicated. 1. Affects the nose landing gear upper and lower toggle pins P/N 28-86128. a. Within the next 300 hours' time in service after the effective date of this AD, unless accomplished within the last 450 hours' time in service, remove the upper and lower nose landing gear toggle pins P/N 28-86128 and inspect for cracks emanating from the ends of the slotted hole located at the center of the pins using Magnaflux (MIL-I-6868) or an FAA- approved equivalent inspection. b. The inspection specified in "a" above shall be repeated at intervals not to exceed 750 hours' time in service from the last inspection. 2. Cracked parts shall be replaced prior to further flight. a. Replacement parts shall be of the same part number or P/N 28-86128-2 or approved equivalent parts. 3. The inspection specified in (1) is not required if: a. P/N 28-86128-2 pins are installed or; b. P/N 28-86128 pins are reworked, in accordance with Canadair Limited Service Information Circular No. 381-CL44 dated October 23, 1974, to P/N 28-86128-2 configuration. 4. The aircraft may be flown in accordance with FAR 21.197 to a base where the inspections or repairs can be performed. 5. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection intervals specified in this AD. Equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. This amendment is effective April 7, 1975.
75-14-04: 75-14-04 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2252 as amended by Amendment 39-2769 is further amended by Amendment 39-2948. Applies to Grumman G-164 S/N 101 through 400, G-164A S/N 401 through 1719, G-164B S/N 1B through 206B, and 208B through 277B, certificated in all categories. 1. Compliance required within 20 hours' time in service after the effective date of this AD, unless already accomplished within the last 80 hours' time in service, and thereafter within 100 hours' time in service from the last inspection. 2. a. For the models G-164 and G-164A inspect the rudder cable P/N A1860- 35, -36 within the cockpit floorboard and chafe strip area for fraying. b. For the Model G-164B inspect the rudder cables P/N A3860-1, -3, within the cockpit floorboard and chafe strip area for fraying. c. Replace any cables that show broken strands. Defective components must be replaced with the same part number or with approved equivalent parts. 3. Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region, may adjust the inspection interval in this AD. 4. Equivalent parts must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region. 5. Aircraft altered to incorporate the pulley and bracket P/N AN220-1 and A1839- 11 and -12, respectively, or altered in accordance with Grumman American Drawing A3371-1, and -3 "Foot Rail Assembly" are considered to have complied with the AD. (Service Bulletin No. 56B dated October 4, 1976, is concerned with this subject). Amendment 39-2252 was effective July 8, 1975. Amendment 39-2769 was effective November 17, 1976. This amendment 39-2948 is effective July 7, 1977.
2012-13-06: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; all Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model 300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes). This AD was prompted by reports of an inoperative fire shut-off valve (FSOV) as a result of damage due to over-length of the bonding lead. This AD requires a one- time detailed inspection for length of the FSOV bonding leads and for contact or chafing of the wires, and corrective actions, if necessary. We are issuing this AD to detect and correct contact or chafing of wires and bonding leads which, if not detected could be a source of sparks in the wing trailing edge, and could lead to an uncontrolled engine fire.
2012-13-04: We are adopting a new airworthiness directive (AD) for certain Empresa Brasileria de Aeron[aacute]utica S.A. (EMBRAER) Model EMB-505 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 an inadequate amount of drain holes in the primary control surfaces (rudder, elevator, and aileron) and their tab surfaces, which may allow water to accumulate in the control surfaces. This condition could cause unbalanced flight control surfaces and reduced flutter margins, which could result in loss of control of the airplane. We are issuing this AD to require actions to address the unsafe condition on these products.
74-18-07: 74-18-07 TELEDYNE CONTINENTAL MOTORS: Amendment 39-1933. Applies to the following Teledyne Continental Model Engines: IO-360-A - Engine serial numbers 20080-R and 20084-R IO-360-C - Engine serial numbers 350015, 350017, 350021, 60228-R, 60229-R, 900308 and 900352. IO-360-D - Engine serial numbers 351048, 351055, 351060, 351075, 351076, 351077, 351080, and 351081. IO-360-H - Engine serial numbers 353124 through 353134. TSIO-360-A - Engine serial numbers 301001, and 301002. TSIO-360-C - Engine serial numbers 300162 and 300170. Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished. To prevent cylinder failure, inspect each cylinder for the assembly date stamp located on the machined surface between the Rocker Box covers. All cylinders date stamped 7-73, 8-73, 9-73, 10-73, and 11-73 must be removed and replaced with airworthy cylinders prior to further flight. This supersedes Amendment39-1780 (39 F.R. 4075) AD 74-3-5. This Amendment becomes effective August 28, 1974.
2012-12-19: We are adopting a new airworthiness directive (AD) for certain the Boeing Company Model 777-200, -200LR, and -300ER series airplanes. This AD was prompted by a report from the manufacturer indicating that the lowered ceiling support structure of Section 41, in airplanes incorporating the overhead space utilization (OSU) option, was found to be under-strength when subjected to a 9.0 g forward load. This AD requires installing new structural members, tie rod(s), and attach fittings on the left and right sides of the lowered ceiling support structure. We are issuing this AD to prevent the forward lowered ceiling panels and support structure from becoming dislodged during a 9.0 g forward load and consequent injury to personnel or interference with an emergency evacuation.
2012-12-17: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model BD-100-1A10 (Challenger 300) airplanes. This AD was prompted by reports of deformation found at the neck of the pressure regulator body on the oxygen cylinder and regulator assembly (CRA). This AD requires an inspection to determine if a certain oxygen CRA is installed and the replacement of affected oxygen CRAs. We are issuing this AD to prevent elongation of the pressure regulator neck, which could result in rupture of the oxygen cylinder, and, in the case of cabin depressurization, oxygen not being available when required.
75-27-03: 75-27-03 HAWKER SIDDELEY AVIATION: Amendment 39-2475. Applies to DH- 114 series airplanes certificated in all categories except those modified in accordance with Hawker Siddeley Modification 1610. Compliance required within the next 400 hours' time in service after the effective date of this AD unless already accomplished. To prevent cracking of the nose gear adjusting screw, replace P/N 4U.493 with P/N 4U.567 in accordance with paragraph No. 5 of Hawker Siddeley Technical News Sheet No. U.16, dated March 19, 1973, or with an FAA-approved equivalent part and procedure. This amendment becomes effective on January 19, 1976.
75-22-03: 75-22-03 HUGHES HELICOPTERS: Amendment 39-2387. Applies to all Hughes Model 369, 369A, 369H, 369HS, 369HE, 369HM, certificated in all categories and military OH- 6A and YOH-6A helicopters incorporating metal tail rotor blades Part Number 369A1613, or -3, in combination with tail rotor drive shaft, Part Number 369A5518. Compliance required within the next 50 hours time in service, after the effective date of this AD unless already accomplished. (a) To prevent possible emergency flight situations resulting from failure of the tail rotor drive shaft, replace drive shaft P/N 369A5518 with drive shaft P/N 369A5518-601 in accordance with Part I, B.3. of Hughes Service Information Notice No. HN-86, dated April 28, 1975, or later FAA-approved revisions. (b) Aircraft may be flown in accordance with FAR 21.197 to a base for the performance of the maintenance described herein. (c) Equivalent modification procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. NOTE: Assure that the record to reflect compliance with this AD is made in aircraft records in accordance with FAR's 91.165 and 91.173. This amendment becomes effective October 24, 1975.
75-26-04: 75-26-04 BEECH: Amendment 39-2458. Applies to Model 200 (BB-2 through BB-71) airplanes. Compliance: Required as indicated, unless already accomplished. To prevent malfunction of the fuel transfer system, within the next 50 hours' time in service after the effective date of this AD, accomplish the following: A) Inspect the P/N 100-920067-1 fuel vent float valve for opening and operation in accordance with the criteria set forth in Beechcraft Service Instruction No. 0772-295 or later FAA-approved revision. (P/N 101-320035-1 baffle, if installed, must be removed to perform this inspection.) B) Replace any fuel vent float valve assembly that does not meet the criteria set forth in Beechcraft Service Instruction No. 0772-295 or later FAA-approved revision with new P/N 100-920067-1 fuel vent float valve assembly. C) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Thisamendment becomes effective December 19, 1975.