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76-05-03: 76-05-03 UNITED AIRCRAFT OF CANADA LIMITED: Amendment 39-2535. Auxiliary Power Unit Model ST6L-73. Compliance required as indicated unless previously accomplished. To preclude leakage of the Sundstrand Aviation 025277 series fuel pump without the part number 5002557 injector cap and screen assembly, accomplish the following: (a) Within the next twenty hours in service after the effective date of this AD, unless previously accomplished, inspect all fuel pumps with less than 250 hours time in service since new in accordance with paragraph 2, Accomplishment Instructions of Pratt & Whitney of Canada Limited Alert Service Bulletin No. 9046 dated August 19, 1975, or approved equivalent inspection. (b) Within the next 250 hours in service after the effective date of this AD, unless previously accomplished, install part number 5002557, injector cap and screen assembly, in accordance with paragraph 2, Accomplishment Instructions of Pratt & Whitney Aircraft of Canada Limited Service Bulletin No. 9043, dated September 2, 1975, or approved equivalent instructions. The aircraft may be flown in accordance with FAR 21.197 to a base where the alteration or inspection can be performed. An equivalent alteration or inspection must be approved by the Chief, Engineering and Manufacturing Branch, of the Eastern Region of the FAA. This amendment is effective March 9, 1976.
75-19-02: 75-19-02 LOCKHEED: Amendment 39-2362 as amended by Amendment 39-2513 and Amendment 39-2625 is further amended by Amendment 39-3158. Applies to all model 382 series airplanes, serial numbers 3946 and 4101 through 4541. On airplane serial numbers 3946 and 4101 through 4298 with 6,300 hours or more total time in service, and on airplane serial numbers 4299 through 4541 with 9,450 hours or more total time in service on the effective date of Amendment 39-3158 unless already accomplished, eddy current inspect the outer wing lower aft beam caps at OWS 54 and 108 in accordance with Hercules Airfreighter Inspection Procedures SMP 515-A Card No. SP-88, revised August 11, 1975. Reinspect at intervals not to exceed 3400 hours time in service from the last inspection until 20,000 hours, (without ECP 954) or 24,000 hours, (with ECP 954) at which time the interval is not to exceed 1700 hours time in service from the last inspection. If a crack or cracks are found, before further flight, contactthe Chief, Engineering and Manufacturing Branch, FAA, Southern Region, Atlanta, Georgia, telephone number 404-526-7428. Before the accumulation of more than 30,000 flight hours, preventive modification shall be installed in accordance with Lockheed Service Bulletin 382-187, or later FAA-Approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. The inspections required by this AD may be discontinued for those airplanes which have been modified in accordance with the above paragraph. Amendment 39-2362 superseded Amendment 39-2249, FR Doc. 75-17068, AD 75-14-05. Amendment 39-2362 was effective September 12, 1975, and was effective June 13, 1975, for all recipients of the telegrams dated June 13, 1975, and August 25, 1975, which contained this amendment. Amendment 39-2513 became effective February 13, 1976. Amendment 39-2625 became effective June 4, 1976. This amendment 39-3158 becomes effective March 20, 1978.
2018-04-09: We are adopting a new airworthiness directive (AD) for Pacific Aerospace Limited Model 750XL 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 incorrectly marked and annunciated low oil pressure indication warnings. We are issuing this AD to require actions to address the unsafe condition on these products.
2013-06-04: We are adopting a new airworthiness directive (AD) for REIMS AVIATION S.A. Model F406 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 fretting (wear and/or chafing) found between the elevator pushrod assembly and the horizontal tail structure, which could cause the elevator pushrod to jam and could result in loss of control. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-10-05: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Model 390 airplanes. This AD requires you to incorporate information into the FAA-approved Airplane Flight Manual (AFM) that would add requirements for "Landing Performance for Operation of the Airplane with Lift Dump Inoperative." This AD is the result of two accidents on the affected airplanes where a contributing factor was the lift dump spoilers failing to deploy when commanded after the initial landing. The FAA previously issued AD 2003-07-09 affecting certain Model 390 airplanes. However, the airplane serial numbers included in this AD were inadvertently omitted from AD 2003-07-09. The actions specified by this AD are intended to require the use of necessary flight information to prevent runway overruns based on insufficient wheel braking if the lift dump spoilers do not operate after landing touchdown. This could result in reduced or loss of control of the airplane. DATES: This AD becomes effective on May 30, 2003. The Director of the Federal Register previously approved the incorporation by reference of certain publications listed in the regulation as of April 7, 2003 (68 FR 16205, April 3, 2003). The Federal Aviation Administration (FAA) must receive any comments on this rule on or before July 2, 2003.
47-49-08: 47-49-08 LOCKHEED: (Was Service Note 8 of AD-763-3.) Applies to All Model 49 Serials Up to and Including 2046. At periods not to exceed 250 hours, inspect the aileron leading edge ribs at Stations 571 and 577, the adjacent leading edge skin and the counterbalance supports for signs of cracks. When cracks are found, install heavier supports, new rib elements, new leading edge skin, and rib reinforcements, as required. When both ribs have been reinforced and heavier supports installed, this periodic inspection may be discontinued. (LAC Service Bulletin 49/SB-162 covers this same subject.)
96-21-12 PL: 96-21-12 BELL HELICOPTER TEXTRON, A DIVISION OF TEXTRON CANADA LTD.: Priority Letter issued on October 11, 1996. Docket No. 96-SW-34-AD. Applicability: Model 407 helicopters, certificated in any category. NOTE 1: This AD applies to each helicopter identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For helicopters that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (d) to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition, or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any helicopter from the applicability of this AD. Compliance: Required immediately upon receipt of this AD. To prevent uncommanded inflight engine shut-downs, accomplish the following: (a) Do not fly the helicopter. (b) Manufacture a placard that states "Flight Of This Helicopter Is Prohibited". The placard shall be manufactured of a material that cannot be easily defaced or erased, and the lettering shall be block-style and at least 2-inches high but not more than 6-inches high. Additionally, the color of the lettering must contrast with the background (color of the placard material) so that it is legible. Install the placard in the pilot-side window of the helicopter. Do not remove the placard from the helicopter until corrective action(s) have been issued by the FAA in the form of an AD, and have been accomplished. (c) Insert a copy of this AD into each BHTC Model 407 helicopter maintenance records. (d) 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, Rotorcraft Certification Office, Rotorcraft Directorate, FAA. Operators shall submit their requests through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Rotorcraft Certification Office. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Rotorcraft Certification Office. (e) Special flight permits will not be issued. Flight testing of a helicopter affected by this AD, by Bell Helicopter Textron, Inc. only, may be permitted if approved by the Manager, Rotorcraft Certification Office, Rotorcraft Directorate, FAA. (f) Priority Letter AD 96-21-12, issued October 11, 1996, becomes effective upon receipt.
2018-02-17: We are superseding Airworthiness Directive (AD) 2012-12-12 and AD 2013-16-26, which applied to all Airbus Model A330-200, A330-200 Freighter, A330-300, A340-200, and A340-300 series airplanes. AD 2012- 12-12 required repetitive inspections of the outer skin rivets of the cargo doors, repair if necessary, and other repetitive inspections. AD 2013-16-26 required repetitive inspections of certain cargo doors, and repair if necessary. This new AD continues to require repetitive inspections, and repair if necessary. This new AD revises the applicability; adds a one-time inspection and adjustment of certain hook gaps; reinforcement of the door frame structure; related investigative and corrective actions if necessary; and a modification, which allows deferring reinforcement of the cargo door structure. This AD was prompted by a determination that a new inspection procedure is necessary to address the unsafe condition. We are issuing this AD to address the unsafe condition on these products.
2013-03-10: We are adopting a new airworthiness directive (AD) for certain Lindstrand Hot Air Balloons Ltd female ACME threaded hose connectors, part numbers HS6139 and HS6144, installed on balloons. 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 insufficient tightness of the threaded hose connector in the assembly area that could result in fuel leakage. We are issuing this AD to require actions to address the unsafe condition on these products.
2003-10-02: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce plc (RR) RB211-524C2-19 and RB211-524C2-B-19 series turbofan engines. This AD requires replacing the existing low pressure (LP) compressor location bearing assembly, intermediate pressure (IP) compressor location bearing, IP compressor bearing support housing, IP compressor rear stub shaft, LP compressor location bearing support, oil transfer connector assembly, hydraulic oil seal housing, and hydraulic oil seal with improved design parts. This AD is prompted by statistical analysis by the manufacturer of in-service premature bearing failures. The actions specified in this AD are intended to prevent LP compressor failure and uncontained disc failures, resulting in damage to the airplane.