Results
2013-04-08 R1: We are revising an airworthiness directive (AD) for certain Diamond Aircraft Industries GmbH Models HK 36 R, HK 36 TS, and HK 36 TTS powered gliders. AD 2013-04-08 required replacement of each elevator bell crank assembly and elevator bell crank mount. This AD retains the actions of AD 2013-04-08 but decreases gliders in the Applicability by removing the Model H-36 from the Applicability. This AD was prompted by reports of installation of an unsuitable self- locking nut on the bell crank of the elevator push rod that can cause failure of the elevator, resulting in loss of control. We are issuing this AD to correct the unsafe condition on these products.
98-23-02: This amendment supersedes Airworthiness Directive (AD) 80-10-01, which applies to certain Cessna Aircraft Company (Cessna) 180 and 185 series airplanes that have either Airglas Engineering Company, Inc., (AECI) Model LW3600-180 (single position) or Model LW3600-180A (two position) fixed penetration wheel skis installed in accordance with Supplemental Type Certificate (STC) SA213AL. AD 80-10-01 requires modifying the ski bungee assemblies, safety cables, and check cables, and their attachments to the airplane and the skis; limiting the maximum airspeed to 160 knots with skis installed; and installing an airspeed limitation placard. This AD is the result of field reports of incidents occurring on the affected airplanes that were in compliance with AD 80-10-01, and the fact that Cessna Model 180K airplanes were inadvertently left out of the existing AD. This AD retains the actions required by AD 80-10-01; requires re-marking the airspeed indicator to display the reduced airspeed limits and placing a certain airplane flight manual (AFM) supplement in the cockpit; and adds Cessna Model 180K airplanes to the Applicability section of the AD. The actions specified by this AD are intended to prevent one or both wheel skis from rotating into a nose-down position during flight, which could result in loss of control of the airplane and/or possible airplane damage during flight or landing operations.
91-18-19: 91-18-19 BEECH: Amendment 39-8022. Docket No. 91-CE-16-AD. Applicability: The following model airplanes, certificated in any category: Models Serial Numbers F33A CE-634 through CE-1536 V35B D-9862 through D-10403 A36 E-825 through E-2578 B36TC EA-1 through EA-509 95-B55, 95-B55A TC-1947 through TC-2456 E55, E55A TE-1078 through TE-1201 58, 58A TH-733 through TH-1609 58P, 58PA TJ-3 through TJ-497 58TC, 58TCA TK-1 through TK-151 Compliance: Required within the next 100 hours time-in-service after the effective date of this AD, unless already accomplished. To prevent malfunctioning pilot and copilot shoulder harnesses that could result in occupant injury during an emergency situation, accomplish the following: (a) Inspect the washers on the "D" ring of the pilot and copilot shoulder harnesses in accordance with the instructions of Beech Service Bulletin (SB) No. 2394, dated December 1990. (b) If the washers installed on the "D" ring do not meet the criteria in the instructions of Beech SB No. 2394, dated December 1990, prior to further flight, replace the washers with part number 100951X060YA. (c) 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. (d) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Wichita Aircraft Certification Office. (e) The inspections and possible replacements required by this AD shall be done in accordance with Beech Service Bulletin No. 2394, dated December 1990. 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 the Beech Aircraft Corporation, P.O. Box 85, Wichita, Kansas 67201-0085. 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 (39-8022, AD 91-18-19) becomes effective on October 21, 1991.
90-12-09: 90-12-09 AIRSHIP INDUSTRIES: Amendment 39-6623. Docket No. 90-CE-09-AD. Applicability: Model Skyship 600 Series (all serial numbers) airships 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 preclude loss of lift capability, accomplish the following: (a) Inspect the attachment of the gaiter to the T-chest, and if double sided tape has been used, prior to further flight install a bonded reinforcement repair in accordance with the instructions specified in Airship Industries Alert Service Bulletin SB Ref 600-53-A311, dated June 10, 1989. (b) Airships may be flown in accordance with FAR 21.197 to a location where this AD can be accomplished. (c) An alternate method of compliance or adjustment of the compliance time which provides an equivalent level of safety, may be approved by the Manager, Brussels Aircraft Certification Office, c/o American Embassy, APO New York 09667-1011. NOTE: 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. All persons affected by this directive may obtain copies of the document referred to herein upon request to Airship Industries, No. 1 Hangar, Cordington, Shortstown, Bedford, England, or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-6623, AD 90-12-09) becomes effective on July 9, 1990.
2013-08-18: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 737-600, -700, -700C, -800, -900 and -900ER series airplanes. This AD was prompted by a report of leaking fuel from the wing leading edge area at the inboard end of the number 5 leading edge slat. This AD requires modifying the fluid drain path in the wing leading edge area, forward of the wing front spar, and doing all applicable related investigative and corrective actions; and installing new seal disks on the latches in the fuel shutoff valve access door. We are issuing this AD to prevent flammable fluids from accumulating in the wing leading edge, and draining inboard and onto the engine exhaust nozzle, which could result in a fire.
2013-08-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 767-300 series airplanes. This AD was prompted by a report that certain airplanes might not have reinforcement straps installed on the center overhead stowage bins in the passenger compartment, and some installed reinforcement straps might not have been bonded. For certain airplanes, this AD requires performing an inspection of reinforcement straps to ensure they are correctly bonded to the center overhead stowage bins, and bonding the reinforcement straps to the center overhead stowage bins if necessary. For certain airplanes, this AD requires installing reinforcement straps on the center overhead stowage bins. We are issuing this AD to prevent missing or incorrectly bonded reinforcement straps, which could result in the center overhead stowage bins breaking loose at forward load levels less than 9g during an emergency landing, causing injury to passengers and delaying emergency evacuation.
98-15-25: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-15-25, which was sent previously to all known U.S. owners and operators of Eurocopter Deutschland GmbH Model EC 135 helicopters by individual letters. This AD supersedes AD 98-09-11, applicable to Eurocopter Deutschland GmbH Model EC 135 helicopters, that required, before further flight, a tail rotor drive shaft vibration survey and installation of a Fenestron Shaft Retrofit Kit; inspecting the tail rotor drive shaft bearing (bearing) attaching lock plates for bent-open tabs, and broken or missing slippage marks; and visually inspecting each bearing support for cracks. This AD requires the same actions as the superseded AD; however, it changes the required compliance time for the repetitive inspections. This amendment is prompted by reports of loose bearings and attachment bolts. This condition, if not corrected, could result in loose bearing attachment bolts, or crackedbearing supports, which could result in loss of drive to the tail rotor and subsequent loss of control of the helicopter.
86-14-51 R1: 86-14-51 R1 THE DeHAVILLAND AIRCRAFT COMPANY OF CANADA, A DIVISION OF BOEING OF CANADA, LTD.: Amendment 39-5423 as amended by Amendment 39-5969. Applies to Model DHC-8-101 series airplanes, Serial Number 003 and subsequent, certificated in any category. Compliance is required as indicated, unless previously accomplished. To preclude the uncommanded deployment of ground spoilers and roll control spoilers in the ground mode, accomplish the following: A. Prior to further flight, lockout circuit breaker ROLL SPLRS CONT, location F6, right essential bus, and circuit breaker GND SPLRS CONT, location C7, left main bus, in accordance with Section A of de Havilland Alert Service Bulletin AB-27-25, dated July 3, 1986. Install a placard in the flight compartment, on the glareshield under the flight/taxi switch, to state the following: "GROUND SPOILERS AND ROLL CONTROL SPOILERS IN GROUND MODE ARE INOPERATIVE." B. Prior to further flight, insert a copy of this AD in the Airplane Flight Manual (AFM) Limitations Section. The elimination of all spoiler functions in ground mode increases landing distance and landing field length required by 15 percent when using flaps at 35 degrees (AFM, Figure 5.8.4.), and 10 percent when using flaps at 15 degrees (AFM Supplement No. 9, Figure 5.8.7.). With all spoiler functions in ground mode inoperative, there is negligible increase in the takeoff distance required and the takeoff run required. C. Within 6 months after the effective date of this amendment, re-establish normal use of all spoilers in the ground mode configuration and remove the operating limitations of paragraphs A. and B., above, by accomplishing the following: 1. Modify the Landing Gear Proximity Switch Electronic Unit (PSEU) in accordance with de Havilland Service Bulletin 8-32-54, Revision B, dated November 20, 1987. 2. Modify the electrical power phase supply for the PSEU BITE Power Circuit, in accordance with de Havilland Service Bulletin 8-32-55, Revision A, dated November 20, 1987. 3. Remove the placard required by paragraph A., above, and reinstate the equipment required to be deactivated by paragraphs A. and B., above, in accordance with the instructions of de Havilland Service Bulletin 8-27-34, Revision C, dated January 8, 1988. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, New York Aircraft Certification Office, FAA, New England Region. All persons affected by this directive who have not already received the appropriate service document from the manufacturer, may obtain copies upon request to The de Havilland Aircraft Company of Canada, A Division of Boeing of Canada, Ltd., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the FAA, New England Region, New York Aircraft Certification Office, 181 South Franklin Avenue, Room 202, Valley Stream, New York. This amendment, 39-5969, amends AD 86-14-51, Amendment 39-5423 effective October 6, 1986, as to all persons except those to whom it was made immediately effective by telegraphic AD T86-14-51 issued July 8, 1986. This amendment, 39-5969, becomes effective August 11, 1988.
60-04-05: 60-04-05 ROLLS-ROYCE: Amdt. 103 Part 507 Federal Register February 17, 1960. Applies to Dart 510 Engines. Compliance required as indicated. In order to prevent failure of impeller shaft, P/N 10543/16719, the following action shall be taken: Beginning April 20, 1960, all impeller shafts, P/N 10543/16719, which have been in operation for 6,000 hours or more, shall be replaced by new impeller shafts of the same part number or by any subsequent approved impeller shafts. (Rolls-Royce Modification 378 covers this subject.)
2022-09-14: The FAA is superseding Airworthiness Directive (AD) 2019-22- 05, which applied to all General Electric Company (GE) CF34-8C model turbofan engines. AD 2019-22-05 required initial and repetitive inspections of the operability bleed valve (OBV) fuel tubes, OBV bleed air manifold link rod assemblies, and the OBV fuel fittings. AD 2019- 22-05 also required replacement of OBVs or related OBV link rod hardware that fail inspection. This AD was prompted by multiple reports of fuel leaks, some leading to engine fires, which have occurred as a result of malfunctions related to the OBV. Additionally, the manufacturer has redesigned the OBV, which terminates the need for the repetitive inspections. This AD requires initial and repetitive inspections of the OBV fuel tubes, OBV bleed air manifold link rod assemblies, and the OBV fuel fittings installed on GE CF34-8C model turbofan engines. This AD requires replacement of OBVs or related OBV link rod hardware that fail inspection. As a terminating action to the repetitive inspections, this AD requires replacement of certain OBVs installed on GE CF34-8C model turbofan engines. This AD also requires replacement of certain OBVs installed on GE CF34-8E model turbofan engines. The FAA is issuing this AD to address the unsafe condition on these products.