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2005-20-07: The FAA adopts a new airworthiness directive (AD) for certain Airbus Model A330-300 series airplanes. This AD requires reinforcing the structure of the center fuselage by installing external stiffeners (butt straps) at frame (FR) 53.3 on the fuselage skin between left-hand and right-hand stringer 13, and related investigative actions. This AD results from a report that, during fatigue tests of the fuselage, cracks initiated and grew at the circumferential joint of FR53.3. We are issuing this AD to prevent fatigue cracking of the fuselage, which could result in reduced structural integrity of the fuselage.
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91-23-03: 91-23-03 AVIONS MUDRY & CIE: Amendment 39-8072. Docket No. 91-CE-58-AD.
Applicability: Model CAP10B Airplanes (serial numbers 01 through 208), certificated in any category.
Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished.
To prevent engine stoppage caused by air entering the inverted flight valve, accomplish the following:
(a) Modify the fuel system in accordance with paragraph 2. ASSEMBLY INSTRUCTIONS of Avions Mudry & Cie Service Bulletin CAP10B No. 13, dated May 14, 1991.
(b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the airplane to a location where the requirements of this AD can be accomplished.
(c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, Middle East office, FAA, c/o American Embassy, 1000 Brussels, Belgium. The request should be forwarded through an FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office.
(d) The modifications required by this AD shall be done in accordance with Avions Mudry & Cie Service Bulletin CAP10B No. 13, dated May 14, 1991. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR Part 51. Copies may be obtained from Avions Mudry & Cie, B.P. 214, 27300 Bernay, France. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 1100 L Street, NW; Room 8401, Washington, DC.
This amendment (39-8072, AD 91-23-03) becomes effective on December 10, 1991.
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94-16-01: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Industrie Model A340-211 and -311 series airplanes. This action requires modifying the bonding leads on the fuel quantity indicating (FQI) probes or the temperature sensor, on the fuel low pressure inlet pipe next to the compensator, and on the jet pump. This amendment is prompted by results of a quality survey, which revealed that there may be insufficient clearance between several bonding leads and certain FQI system probes or the temperature sensor, and between the bonding leads and the FQI probes and the compensator. The actions specified in this AD are intended to eliminate such insufficient clearance, which could lead to electrical arcing and a resultant fire in the event of a lightning strike.
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2005-20-05: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 767-200 and 767-300 series airplanes. This AD requires performing a general visual inspection to determine the part number of the I-beams of the center overhead stowage bin modules to identify I-beams having 9.0g (gravitational acceleration) tie rods attached and to determine the configuration of the center overhead stowage bin modules. For certain center overhead stowage bin modules, this AD requires installing support straps. This AD results from tests conducted by the airplane manufacturer. We are issuing this AD to prevent failure of the attachment of the 9.0g tie rods to the center overhead stowage bin modules. This failure could result in collapse of those stowage bin modules, and consequent injury to passengers and crew and interference with their ability to evacuate the airplane in an emergency.
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47-32-02: 47-32-02 BELL: (Was Mandatory Note 2 of AD-1H-1.) Applies Only to Model 47B Serial Numbers 2 Through 6 and 8 Through 28.
Compliance required not later than next 25-hour inspection after September 15, 1947.
The correct amount of fixed ballast for the Model 47B helicopters, as listed in Bell Service Bulletin 47C27, dated June 25, 1947, should be installed in accordance with the instructions also contained in that Bulletin. Compliance is required in order that the correct center of gravity range may be maintained.
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47-32-12: 47-32-12 BELL: (Was Mandatory Note 12 of AD-1H-1.) Applies to Models 47B and 47B3 Helicopters.
Compliance required not later than the next 25-hour inspection after September 15, 1947.
In order to provide more strength in the lateral cycle control system, the disc links should be replaced with forward and aft links, 47-725-047.
(Bell Service Bulletin 47C35 dated June 18, 1947, also covers this same subject.)
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98-12-11: This amendment adopts a new airworthiness directive (AD) that applies to certain British Aerospace Jetstream Model 3101 airplanes. This AD requires modifying the emergency hydraulic hand-pump by increasing the length of the access aperture. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for the United Kingdom. The actions specified by this AD are intended to prevent difficulty accessing the emergency hydraulic hand-pump because of the current design, which, in the event of a hydraulic system failure, could result in the inability to operate the flaps and landing gear.
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94-24-11: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, that requires a one-time inspection for cracks in the tail rotor drive shaft hanger bearing support brackets (brackets), and repair or replacement, as necessary. This amendment is prompted by reports of cracks in the bend radius of the brackets. The actions specified by this AD are intended to prevent misalignment of the tail rotor drive shaft, failure of the tail rotor drive shaft system, loss of control of the tail rotor, and subsequent loss of control of the helicopter.
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2005-19-25: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This AD requires repetitive eddy current inspections for cracks of the countersunk rivet holes in the lower lobe, adjacent to the radio altimeter cutouts; additional inspections, for certain airplanes, for cracks and/or corrosion; and further investigative and corrective action if any crack is found. This AD also provides an optional terminating action for the repetitive inspections. This AD results from reports of cracks in the fuselage skin of the lower lobe. We are issuing this AD to detect and correct fatigue cracks of the countersunk rivet holes, which could result in cracks of the fuselage skin of the lower lobe, and consequent rapid depressurization of the cabin.
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47-51-07: 47-51-07 CURTISS-WRIGHT Applies to all C-46 Series aircraft.
Compliance required not later than March 1, 1948, and each 1,000 hours of operation thereafter.
Inspect the landing gear drag strut support structure inside nacelle to determine if landing gear drag strut No. 20-720-1018 attaching bolts at the 70 percent spar have loosened and if angle assembly 20-720-1024-1 and bulkhead assemblies 20-720-1021-1 and 20-720-1023-6 are loose. All defective parts, loose or sheared attachment rivets should be replaced and loose bolts tightened.
To accomplish the above, it is necessary to remove one outer panel or provide an access door in order to gain access to the interior of the center panel.
(Curtiss-Wright Service Information Letter No. 735 dated August 20, 1947, covers an acceptable wing panel door installation.)
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