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86-07-02 R1: 86-07-02 R1 PILATUS BRITTEN-NORMAN LTD: Amendment 39-10171; Docket No. 86-CE-23-AD. Revises AD 86-07-02, Amendment 39-5382. Applicability: Models BN2A MK. 111, BN2A MK. 111-2, and BN2A MK. 111-3 airplanes (all serial numbers), certificated in any category. NOTE 1: This AD applies to each airplane 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 airplanes that have been 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 (f) 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 prior to further flight after the effective date of this AD (see NOTE 2) or within 100 hours time-in-service (TIS) after the last inspection accomplished in accordance with AD 86-07-02, whichever occurs later, and thereafter at intervals not to exceed 100 hours TIS. NOTE 2: The "prior to further flight after the effective date of this AD" compliance time was the original initial compliance time of AD 86-07-02, and is being retained to provide credit and continuity for already-accomplished and future inspections. To prevent failure of the main landing gear caused by cracks in the torque link assembly area, which could lead to loss of control of the airplane during landing operations, accomplish the following: (a) Inspect the junction of the torque link lug and upper case for cracks (using a 10- power magnifying glass or by dye penetrant methods) in accordance with Fairey Hydraulics Limited Service Bulletin (SB) 32-7, Issue 3, dated January 30, 1990; or Fairey Hydraulics SB 32- 10, Issue 2, dated November 10, 1992, as applicable. Pilatus Britten-Norman SB BN-2/SB. 173, Issue 3, dated November 16, 1990, references Fairey Hydraulic Limited SB 32-7; and Pilatus Britten-Norman SB BN-2/SB.209, Issue 1, dated November 30, 1992, references Fairey Hydraulic Limited SB 32-10. (b) If cracked parts are found during any of the inspections required by this AD, prior to further flight, replace the cracked parts with airworthy parts in accordance with the applicable maintenance manual. (c) If the landing gear is replaced, only equal pairs of the same manufacturer are approved as replacement parts. Mixing of different manufacturer landing gears is not authorized. (d) The intervals between the repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these actions along with other scheduled maintenance on the airplane. (e) Special flight permits maybe 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 inspection requirements of this AD can be accomplished. (f) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Small Airplane Directorate, 1201 Walnut, suite 900, Kansas City, Missouri 64106. (1) The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Small Airplane Directorate. (2) Alternative methods of compliance approved for AD 86-07-02 are considered approved as alternative methods of compliance for this AD. NOTE 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Small Airplane Directorate. (g) The inspections required by this AD shall be done in accordance with Fairey Hydraulics Limited Service Bulletin 32-7, Issue 3, dated January 30, 1990, or Fairey Hydraulics Service Bulletin 32-10, Issue 2, dated November 10, 1992, as applicable. 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 Fairey Hydraulics Limited, Claverham, Bristol, England; or Pilatus Britten-Norman Limited, Bembridge, Isle of Wight, United Kingdom PO35 5PR. Copies may be inspected at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment (39-10171) revises AD 86-07-02, Amendment 39-5382. (i) This amendment becomes effective on November 28, 1997.
86-07-04: 86-07-04 SHORT BROTHERS, LTD.: Amendment 39-5272. Applies to Models SD3- 30 and SD3-60 airplanes as listed in Short Brothers, Ltd. Service Bulletins SD3-27-29, dated April 1985 (for SD3-30 airplanes), and SD360-27-06, dated April 1985 (for SD3-60 airplanes), certificated in any category. To prevent the loss of elevator control, accomplish the following within the next 90 days after the effective date of this AD, unless already accomplished: 1. Modify the elevator torque tube assembly in accordance with Short Brothers, Ltd. Service Bulletin SD3-27-29, dated April 1985 (for SD3-30 airplanes), or SD360-27-06, dated April 1985 (for SD3-60 airplanes). 2. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. 3. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment ofinspections and/or modifications required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Shorts Aircraft, 1725 Jefferson Davis Highway, Suite 510, Arlington, Virginia 22202. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective May 8, 1986.
2012-07-04: We are adopting a new airworthiness directive (AD) for certain Cessna Aircraft Company Model 680 airplanes. This AD was prompted by a false cross-feed command to the right-hand fuel control card, due to the cross-feed inputs on the left- and right-hand fuel control cards being connected together and causing an imbalance of fuel between the left and right wing tanks. This AD requires adding diodes to the fuel cross-feed wiring, and revising the airplane flight manual to include procedures to use when the left or right generator is selected OFF. We are issuing this AD to prevent lateral imbalance of the airplane, resulting from uncontrolled fuel cross-feed, which can be corrected by deflecting the aileron trim; deflecting the aileron trim increases the pilot's workload and could exceed the airplane's limitation in a short period of time, resulting in reduced controllability of the airplane.
97-23-17: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) 90, 100, 200, and 300 series airplanes. This action requires inspecting gray, blue, or clear Ethylene Vinyl Acetate (EVA) tubing near the co-pilot's foot warmer for collapse or deformity. If the tubing is collapsed or deformed, this action requires replacing and re-routing the tubing. This EVA tubing is used on the pneumatic de-ice indicator lines and the pressurization control system pneumatic lines that provide vacuum to the outflow safety valves that depressurize the airplane. This action is the result of several reports of collapsed EVA tubing. The actions specified by this AD are intended to prevent a loss of vacuum to depressurize the airplane cabin, which could result in personal injury to the door operator; and to prevent malfunction of the de-ice indicator system, which could cause the pilot to immediately exit icing conditions.
82-13-01: 82-13-01 BENDIX: Amendment 39-4405. Applies to Bendix Engine Products Division's S-1200 series magnetos which have green distributor blocks and do not have the letter "R" metal stamped on the identification plate as described under "Identification" in Bendix Service Bulletin No. 613. Compliance required as indicated unless already accomplished. To reduce the possibility of magneto and engine malfunction resulting from loose distributor block bushings, accomplish the following: (a) Comply with the inspection, replacement, and identification procedures outlined under "Detailed Instructions" shown in Bendix Service Bulletin No. 613, dated April 1981, or later approved revisions in accordance with the following schedule: MAGNETO TIME IN SERVICE SINCE NEW OR OVERHAUL ACCOMPLISH Less than 1000 hours Inspect within the next 25 hours in service and every 25 hours in service thereafter, unless replaced with new "Gripper Bushing" distributor block. 1000 hoursor more but less service than 1900 hours Inspect within the next 100 hours in service unless replaced with new "Gripper Bushing" distributor block. 1900 hours or more Replace the distributor block with new "Gripper Bushing" distributor block within the next 100 hours in service. Any distributor block discovered having a loose bushing must be replaced before further flight. (b) If compliance with Paragraph (a) reveals the distributor block to be contaminated with brass filings or bronze colored dust, inspect the engine as follows: (1) Observe engine pistons through spark plug holes for evidence of burning. (2) Check valve dry tappet clearance per engine manufacturer's instructions. If piston damage or lower than specified dry tappet clearance is present, the engine must be inspected and maintained in accordance with the engine manufacturer's instructions for continued airworthiness. Make an engine log entry of each compliance with Paragraph (a) including the magneto serial number. Equivalent means of compliance may be approved by the Chief of the New York Aircraft Certification Office, ANE-170, Federal Aviation Administration (FAA), New England Aircraft Certification Division, Federal Building, JFK International Airport, Jamaica, New York 11430. As permitted by FAR 21.197, aircraft may be flown to a base where maintenance required by this AD can be accomplished. This amendment becomes effective June 28, 1982.
2022-04-04: The FAA is adopting a new airworthiness directive (AD) for certain Continental Aerospace Technologies, Inc. C-125, C145, IO-360, IO-470, IO-550, O-300, O-470, TSIO-360, TSIO-520 series model reciprocating engines and certain Continental Motors IO-520 series model reciprocating engines with a certain oil filter adapter installed. This AD was prompted by reports of two accidents that were the result of power loss due to oil starvation. This AD requires replacing the oil filter adapter fiber gasket (fiber gasket) with an oil filter adapter copper gasket (copper gasket). The FAA is issuing this AD to address the unsafe condition on these products.
2022-04-02: The FAA is adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000 model turbofan engines. This AD was prompted by reports of high levels of wear on the seal fins on a small number of certain high-pressure turbine triple seals. This AD requires manual deactivation of the modulated air system (MAS) control valves. The FAA is issuing this AD to address the unsafe condition on these products.
2012-04-14: We are adopting a new airworthiness directive (AD) for RB211- Trent 800 series turbofan engines. This AD requires inspecting the front combustion liner head section for cracking, and if found cracked, removing the front combustion liner head section from service at the next shop visit. This AD was prompted by mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. Specifically, routine inspections revealed cracking on the head sections of two RB211-Trent 800 front combustion liners. We are issuing this AD to prevent uncontained engine failure and damage to the airplane.
97-21-09: This amendment supersedes existing airworthiness directive (AD) 96-24-09, applicable to Allison Engine Company Model 250-C47B turboshaft engines, that currently requires replacing the engine main electrical harness assembly with an improved assembly, disabling the overspeed solenoid, inspecting the engine control unit (ECU) internal PW10 voltage to determine electrical noise characteristics, and replacing units not considered serviceable. In addition, the existing AD requires adding a placard to the helicopter instrument panel notifying the pilot that the overspeed protection system is disabled and removes a placard which was required by priority letter AD 96-21-12; revises the Bell Helicopter Textron, A Division of Textron Canada Ltd. (BHTC) Model 407 Rotorcraft Flight Manual (RFM); and requires maintenance actions to clear the ECU of faults prior to each flight. This amendment continues to require replacing the engine main electrical harness assembly with an improved assembly, but adds the requirements to install a new hydromechanical unit (HMU) and ECU, removing the placard notifying the pilot that the overspeed protection system is disabled, and revises the BHTC Model 407 RFM. This amendment is prompted by the development of overspeed protection system modifications to reactivate the overspeed solenoid in conjunction with raising the power turbine overspeed trip point and revising the overspeed system to default to a minimum fuel flow in the event of its activation. The actions specified by this AD are intended to prevent uncommanded inflight engine shutdowns, which can result in autorotation, forced landing, and possible loss of the helicopter.
87-16-03: 87-16-03 AIRBUS INDUSTRIE: Amendment 39-5623. Applies to Model A300 B2 and B4 series airplanes, certificated in any category. To prevent the development of cracks which can lead to wing skin failure, accomplish the following within 90 days after the effective date of this AD, or upon reaching the threshold indicated below, whichever occurs later, unless already accomplished: A. Inspect for cracks in the top skin of each wing at the level of rib 9 between front and rear spars, prior to the accumulation of 17,000 landings for B2 series airplanes, and prior to the accumulation of 14,200 landings for B4 series airplanes, in accordance with the accomplishment instructions of Airbus Industrie (AI) Service Bulletin A300-57-118, Revision 1, dated March 29, 1984. Thereafter, repeat the inspections at intervals not to exceed 7,600 landings. B. If cracks are found during the inspections required by paragraph A., above, follow procedures described in Paragraph 1.C.(5) of AI Service Bulletin A300-57-118, Revision 1, dated March 29, 1984. C. Incorporation of AI Modification 2099, as described in Airbus Service Bulletin A300-57-077, Revision 1, dated December 15, 1979, which replaces clearance fit HI-LOK bolts with taperlock bolts, constitutes terminating action for the inspection requirements of this AD. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspections required by this AD. All persons affected by this directive who have not already received the appropriate service document from the manufacturer may obtain copies upon request to Airbus Industrie, Airbus Support Division, Centrecda, Avenue Didier Daurat, 31700 Blagnac,France. This document may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective September 4, 1987.