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54-19-01: 54-19-01 PIPER: Applies to Models PA-18A and PA-18A Restricted Category Aircraft With Dusting Venturi, Up to and Including Serial Number 18-3752.
Compliance required not later than October 15, 1954.
There have been several instances of excessive CO concentration in the cockpit when the dusting venturi is used. Such contamination has serious adverse effects upon pilot reaction. To prevent CO from entering the cockpit, a new trim plate should be installed and a new brake line cover plate should be placed over the brake line where the line enters the bottom of the fuselage.
(Piper Service Letter No. 225, dated August 23, 1954, covers the same subject.)
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2017-19-12: We are superseding Airworthiness Directive (AD) 2014-13-17, which applied to all Airbus Model A300 series airplanes; Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4- 605R Variant F airplanes (collectively
[[Page 43672]]
called Model A300-600 series airplanes); and Airbus Model A310 series airplanes. AD 2014-13-17 required repetitive functional tests of the circuit breakers for the fuel pump power supply, and replacement of certain circuit breakers. This new AD requires installation of fuel pumps having a new standard, which terminates the repetitive functional tests. This AD was prompted by our determination that installation of a newly developed fuel pump standard will better address the unsafe condition. We are issuing this AD to address the unsafe condition on these products.
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2017-19-03: We are adopting a new airworthiness directive (AD) for all Dassault Aviation Model MYSTERE-FALCON 900 airplanes. This AD was prompted by a determination that new or more restrictive maintenance requirements and/or airworthiness limitations are necessary. This AD requires revising the maintenance or inspection program, as applicable, to incorporate new or more restrictive maintenance requirements and/or airworthiness limitations. We are issuing this AD to address the unsafe condition on these products.
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2017-18-15: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 B4-600R and Model A300 F4-600R series airplanes; Model A300 B4-603, B4-622, and C4-605R Variant F airplanes; and Model A310-203, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by an evaluation by the design approval holder indicating that a section of the fuselage structure above the forward cargo door is subject to widespread fatigue damage (WFD). This AD requires an inspection for cracks of the fastener and tooling holes at certain locations and a check of the diameter of the holes, and repair or modification of the affected fuselage structure if necessary. We are issuing this AD to address the unsafe condition on these products.
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77-13-07: 77-13-07 BEECH: Amendment 39-2932. Applies to Model 200 (Serial Numbers BB-2 thru BB-250) airplanes certificated in all categories.
Compliance: Required as indicated, unless already accomplished.
To assure that wings will carry the 50 feet/second gust design loads, within 50 hours' time in service after the effective date of this AD, accomplish the following:
A) With aileron control system pinned in the neutral position rerig the droop of right and left aileron to zero degrees, with a tolerance of plus one-half degree up, minus zero degrees down in accordance with Beechcraft Service Instructions Number 0906 or later approved revisions.
B) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
This amendment becomes effective July 1, 1977.
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55-13-01: 55-13-01 PIPER: Applies to Model PA-23, Serial Numbers 23-160 to 23-162 Inclusive, 23-166 to 23-168 Inclusive, 23-170, 23-172, 23-177, 23-193 to 23-219 Inclusive, 23-221 to 23- 224 Inclusive, 23-226 to 23-229 Inclusive, 23-231 to 23-234 Inclusive, and 23-237.
Compliance required by August 1, 1955.
It has been found that all the PA-23 Models listed above have installed two flexible fuel valve controls that have been found to flex excessively at the splice. The addition of an idler bellcrank should be accomplished by the use of Piper Kit No. 754 103 and the instructions included. Owners of PA-23's with auxiliary fuel tanks must not operate the auxiliary fuel system until this modification has been accomplished.
(Piper Immediate Action Service Bulletin No. 139 applies to this malfunction.)
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2017-18-19: We are adopting a new airworthiness directive (AD) for all Airbus Model A310-203, -204, -221, -222, -304, -322, -324, and -325 airplanes. This AD was prompted by reports of cracking in the drainage holes on the lower skin panel in the center wing box between frames (FR) 42 and FR46. This AD requires repetitive rotating probe inspections for cracking of the trellis boom drainage holes, the holes in the stringers bottom, and the holes of the inner pump, and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
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2017-18-16: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-700 and -700C series airplanes. This AD was prompted by a report that, for certain airplanes, the nose-up pitch trim limit and associated warning will allow the horizontal stabilizer position to be set outside acceptable limits for a mis-trimmed takeoff condition. This AD requires, depending on airplane configuration, replacing certain pitch trim light plates, relocating certain position warning horn switches, revising certain software, removing a certain placard, and doing related investigative and corrective actions if necessary. We are issuing this AD to address the unsafe condition on these products.
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53-04-01: 53-04-01 PIPER: Applies to All Model PA-18 Aircraft Which Have Not Had the Control Stick Retention Device Modified to Incorporate a Through Bolt.
Compliance required by April 1, 1953.
In order to prevent the control stick inadvertently pulling out of the socket, continue the existing hole for the retention pin on the quick detachable control stick spring device through the control stick and socket and install an AN 3-14 or AN 3-14A through bolt.
(Piper Service Letter No. 162 dated March 6, 1951, covers this same subject.)
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54-02-02: 54-02-02 FEDERAL SKIS: Applies to All Universal (Stinson) 108 and Cessna 170, 170A and 170B Airplanes Equipped With Federal Models AWB-2500 and AWB-2500A Wheel Skis and Piper PA-20 Airplanes Equipped With Federal Model AWB-2100 Wheel Skis.
Compliance required as soon as possible but not later than February 15, 1954.
To preclude the possibility of the ski dropping down against the mechanical rigger and possible subsequent damage to the aircraft structure, the rigging arrangement must be revised in accordance with Federal Aircraft Works Drawing No. 11D1077.
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