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2015-16-07 R1: We are adopting a new airworthiness directive (AD) for REIMS AVIATION S.A. Model F406 airplanes. This AD revises AD 2015-16-07, which required inspection of the left-hand and right-hand rudder control pedal torque tubes, and, depending on findings, replacement with a serviceable part. This AD retains the actions of AD 2015-16-07 and adds additional acceptable serviceable replacement parts. The AD was prompted by reports of detachment of the pilot's rudder control pedal in flight. We are issuing this AD to require actions to address the unsafe condition on these products.
76-10-04: 76-10-04 START & FLUG: Amendment 39-2612. Applies to H101 "Salto" gliders, certificated in all categories. Compliance is required as indicated unless already accomplished. To prevent possible failure of the cockpit canopy locking device and the consequent inability of the pilot to use his parachute, accomplish the following: (a) Within the next 10 hours time in service after the effective date of this AD, either (1) Install an operating limitations placard on the instrument panel in full view of the pilot to read as follows: "ACROBATIC MANEUVERS PROHIBITED;" or (2) Modify the cockpit canopy fastening mechanism by installing polyamide stop blocks on both canopy fastening mechanisms in accordance with Start & Flug GmbH Technical Note No. 101-8, dated May 1, 1974 and Drawing No. 101-14-34, undated, or FAA-approved equivalents. (b) The placard specified in paragraph (a)(1) of this AD, if installed, may be removed upon the incorporation of the modification described in paragraph (a)(2) of this AD. This amendment becomes effective May 27, 1976.
2000-18-13: This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter Canada Ltd. Model BO 105 LS A-3 helicopters. That AD currently requires, before further flight, creating a component log card or equivalent record and determining the calendar age and number of flights on each tension-torsion (TT) strap, and inspecting and removing, as necessary, certain unairworthy TT straps. This amendment establishes a life limit for certain main rotor TT straps. This amendment is prompted by an accident in which a main rotor blade (blade) separated from a Eurocopter Deutschland GMBH (ECD) Model MBB-BK 117 helicopter due to fatigue failure of a TT strap. The same part-numbered TT strap is used on the Model BO 105 LS A-3 helicopters. The actions specified by this AD are intended to prevent fatigue failure of a TT strap, loss of a blade, and subsequent loss of control of the helicopter.
85-17-07: 85-17-07 CESSNA: Amendment 39-5125. Applies to the following Cessna airplanes certificated in any category: MODEL SERIAL NUMBER U206F/TU206F S/N U20601071 thru U20603521 U206G/TU206G S/N U20603522 thru U20604649 207/T207 S/N 20700001 thru 20700315 207A/T207A S/N 20700363 thru 20700767 Compliance: Required within the next 100 hours time-in-service after the effective date of this AD unless already accomplished. To prevent a possible failure in the wing rear spar on airplanes that have had the full spar or inboard end of the spar replaced, accomplish the following: (a) Visually inspect the airplane in accordance with Cessna Single Engine Service Bulletin SEB85-9 dated May 3, 1985. If the P/N 1222111-1 doubler is missing, prior to further flight repair the spar in accordance with SEB85-9. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent method of compliance with this AD may be used if approved by Manager, Wichita Aircraft Certification Office, Federal Aviation Administration, 1801 Airport Road, Room 100, Wichita, Kansas 67209; Telephone (316) 946-4400. All persons affected by this directive may obtain copies of the document referred to herein upon request to Cessna Aircraft Company, Post Office Box 1521, Wichita, Kansas 67201 or FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. This amendment becomes effective on September 30, 1985.
2000-18-09: This amendment adopts a new airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 412, 412EP, and 412CF helicopters. This AD requires inspecting the upper left-hand cap angle (cap angle) and adjacent structure for a crack and, before further flight, replacing any cracked cap angle and repairing any crack in the adjacent structure. This AD is prompted by a report of a fatigue crack in a tailboom attachment cap angle. The actions specified in this AD are intended to prevent failure of a cap angle, loss of the tailboom, and subsequent loss of control of the helicopter.
2000-18-10: This amendment adopts a new airworthiness directive (AD) for Kaman Model K-1200 helicopters. This action requires replacing certain unairworthy sprag clutches with airworthy sprag clutches. This amendment is prompted by two incidents of sprag clutch failure during external load operations. The actions specified in this AD are intended to prevent a malfunctioning transmission clutch, loss of drive to the main rotor system, and subsequent loss of control of the helicopter.
79-20-04: 79-20-04 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-3576. Applies to all L-1011-385-1, L-1011-385-1-14, and L-1011-385-1-15 series airplanes certificated in all categories. Compliance required as indicated. To provide a warning to the flight crew of an occurrence of a potentially hazardous jam in the elevator drive system prior to takeoff, and thus prevent takeoff with a possible jammed elevator drive system on the horizontal stabilizer of the primary pitch control system which can result in degradation of the airplane controllability, accomplish the following: (a) Within the next ten (10) days after the effective date of this AD, unless the elevator drive system jam warning system of paragraph (b) is installed and is operational on all aircraft of each operator's fleet, initiate the following check program: (1) Prior to each takeoff, conduct an exterior visual check of the elevator/stabilizer surface positions after the full aft controls check and with the control column full forward to assure there is no obvious discrepancy between elevator positions. The pilot-in- command shall be informed of the results of this check. NOTE: This check can be accomplished with any one single hydraulic system pressurized by any main hydraulic system pump. (2) If obvious discrepancy is noted, correct prior to further flight. (3) No further full aft control column movement may be performed prior to takeoff. A placard must be installed in the flight station in full view of the pilot to inform the pilot of the requirements of this subparagraph. (b) On or before July 1, 1981, unless already accomplished, install the elevator drive system jam warning system in accordance with FAA approved Lockheed-California Company Service Bulletin 093-27-174, dated August 3, 1979. The visual exterior checks of paragraph (a), above, may be discontinued upon installation and operation of the warning system on all aircraft of each operator's L-1011 fleet. (c) All elevator surface jam conditions indicated by the warning system of paragraph (b) must be corrected prior to further flight. (d) If the elevator drive system jam warning system is not fully operative prior to initiation of flight operations, the aircraft may be allowed to dispatch provided the visual exterior check of paragraph (a) is accomplished. (e) Alternative checks, installations or other actions which provide an equivalent level of safety may be used when approved by the Chief, Aircraft Engineering Division, FAA Western Region. This amendment becomes effective October 11, 1979.
2000-18-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models A65, A65-8200, 65-B80, 70, 95-A55, 95-B55, 95-C55, D55, E55, 56TC, A56TC, 58, 58P, 58TC, 95-B55B (T42A) airplanes. This AD requires replacement of certain elevator skin assemblies that Raytheon shipped from January 1, 1999, through December 31, 1999, and prevents the future installation of these elevator skin assemblies. This AD authorizes the pilot to check the logbooks to determine whether one of these elevator skin assemblies is installed. This AD is the result of reports that certain elevator skin assemblies did not receive a 250-degree Fahrenheit bake operation after corrosion treatment, thus making the skin susceptible to separation from the elevator assembly. The actions specified by this AD are intended to detect and correct potential elevator skin separation, which would lead to a reduction in static strength capability with continued operation. This could then result in potential airplane flutter with consequent loss of control of the airplane. The Federal Aviation Administration (FAA) must receive any comments on this rule on or before October 27, 2000.
2000-18-06: This amendment adopts a new airworthiness directive (AD), that is applicable to Allison Engine Company AE 3007A and AE 3007C series turbofan engines with certain full authority digital electronic controls (FADEC's), listed by hardware serial number (SN), installed. This action requires inspections of installed FADEC's before further flight to be sure that no more than one engine with suspect FADEC's is installed on the same airplane, and eventual replacement of all of the suspect FADEC's with serviceable FADEC's. This amendment is prompted by reports of uncommanded in-flight shutdowns of engines. The actions specified in this AD are intended to prevent an uncommanded in-flight engine shutdown and the potential for an in-flight dual-engine shutdown caused by a potential hardware failure mode in some AE 3007 series FADEC's.
97-12-01: 97-12-01 CESSNA AIRCRAFT COMPANY: Amendment 39-10044. Docket 97-NM-101-AD. Applicability: Model 650 airplanes, having serial numbers 650-0174 through 650-0241 inclusive, 650-7001 through 650-7006 inclusive, and 650-7008 through 650-7076 inclusive, certificated in any category. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been otherwise modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it. Compliance: Required as indicated, unless accomplished previously. To prevent electrical arcing of the alternating current wire and consequent fire hazard, accomplish the following: (a) Within 25 hours time-in-service after the effective date of this AD, accomplish paragraphs (a)(1), (a)(2), and (a)(3) of this AD, in accordance with the Accomplishment Instructions of Cessna Service Bulletin SB650-24-57, dated May 15, 1997. (1) Perform a visual inspection to detect discrepancies (i.e., improper clearance, wear, and damage) of the wire bundle assembly from point 1 to point 2, in accordance with the service bulletin. If any discrepancy is detected, prior to further flight, replace the wire bundle assembly with a new wire bundle assembly or install a spiral wrap, as applicable, in accordance with the service bulletin. (2) Perform a visual inspection to detect discrepancies (i.e., chafing, rubbing, nicks, scratches, and burn marks) of the hydraulic pump suction line in the area above the baggage compartment, in accordance with the service bulletin. If any discrepancy is detected, prior to further flight, repair it in accordance with the service bulletin. (3) Modify the supports for the wire bundle cable assembly and the supports for the hydraulic pump suction line in accordance with the service bulletin. (b) 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, Wichita Aircraft Certification Office (ACO), FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Wichita ACO. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (d) The inspections and modification shall be done in accordance with Cessna Service Bulletin SB650-24-57, dated May 15, 1997. 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 Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Wichita Aircraft Certification Office, Small Airplane Directorate, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on June 19, 1997.