Results
2019-15-05: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) Trent 1000-AE3, Trent 1000- CE3, Trent 1000-D3, Trent 1000-G3, Trent 1000-H3, Trent 1000-J3, Trent 1000-K3, Trent 1000-L3, Trent 1000-M3, Trent 1000-N3, Trent 1000-P3, Trent 1000-Q3 and Trent 1000-R3 engines. This AD requires removal of the affected high-pressure turbine (HPT) disk front cover plate before reaching its new life limit. This AD was prompted by a recent analysis that determined the HPT disk front cover plate may have a safe life below its declared life limit. The FAA is issuing this AD to address the unsafe condition on these products.
95-25-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Fokker Model F28 Mark 0100 series airplanes. This action requires inspection(s) to detect cracks of the fuselage-mounted half of hinge assemblies of the small cargo door, and replacement of any cracked hinge assembly with a new hinge assembly. This amendment is prompted by a report that the hinges of the small cargo door on these airplanes are made of a material that is sensitive to stress corrosion cracking. The actions specified in this AD are intended to prevent failure of the hinges of the small cargo door due to stress corrosion cracking, which could result in opening and/or separation of the door while the airplane is in flight, and resultant rapid decompression and/or structural damage to the airplane.
2007-01-08: The FAA is adopting a new airworthiness directive (AD) for certain Bombardier Model DHC-8-400 series airplanes. This AD requires inspecting for fouling and chafing damage of the outboard brake control cable of the main landing gear, replacing the control cable if necessary, reworking the control cable cover, and, if applicable, manufacturing/installing an offset plate on the control cable cover. This AD results from a review of brake control cable operation conducted by the manufacturer. We are issuing this AD to prevent abrasion and wear of the outboard brake control cable, which could lead to cable separation and reduced control of airplane braking.
97-06-13: 97-06-13 ROLLS-ROYCE PLC: Amendment 39-9970. Docket 97-ANE-09. Applicability: Rolls-Royce plc (R-R) RB.211 Trent 800 series turbofan engines, installed on but not limited to Boeing 777 series aircraft. Note 1: This airworthiness directive (AD) applies to each engine 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 engines 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 (d) 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 loss of oil, that could cause an engine fire, and inflight engine shutdowns and airplane diversions caused by oil loss and from bearing failures, accomplish the following: (a) Inspect angle drive upper shroud tubes as follows: (1) Within 50 CIS after the effective date of this AD, visually inspect and measure the frettage and fluorescent penetrant inspect (FPI) for cracks the angle drive upper shroud tubes in accordance with R-R Service SB No. RB.211-72-C089, Revision 1, dated January 24, 1997. (2) Thereafter, at intervals not to exceed 50 CIS since last inspection, visually inspect and measure the frettage and FPI for cracks the angled drive upper shroud tubes, in accordance with R-R SB No. RB.211-72-C089, Revision 1, dated January 24, 1997. (3) Prior to further flight, remove from service angled drive upper shroud tubes that exhibit frettage measured in excess of 0.020 inches, or any cracks, and replace with serviceable parts. (4) Installation of an improved angled drive upper shroud tube with a lower splitter fairing with revised sealing in accordance with R-R SB No. RB.211-72-C114, dated February 6, 1997, constitutes terminating action to the inspection requirements of paragraphs (a)(1), (a)(2), and (a)(3) of this AD. (5) Prior to initiation of ETOPS, or prior to September 30, 1997, whichever occurs first, install an improved angled drive upper shroud tube with a lower splitter fairing with revised sealing in accordance with R-R SB No. RB.211-72-C114, dated February 6, 1997. (b) Inspect the intermediate gearbox housing (IGH) and external gearbox lower bevel box (LBB) housing as follows: (1) Within 5 CIS after the effective date of this AD, perform an initial visual inspection of the IGH and LBB housing for cracks, in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (2) Within 10 CIS after the effective date of this AD, perform an initial FPI of the IGH for cracks, in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (3) Thereafter, at intervals not to exceed 5 CIS since last visual inspection, visually inspect the IGH and LBB housing for cracks, and at intervals not to exceed 10 CIS since last FPI, FPI the IGH, in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (4) Within 10 CIS after the effective date of this AD, perform an FPI of the IGH for porosity in accordance with R-R Mandatory SB No. RB.211-72-C129, Revision 2, dated March 21, 1997. (5) Within the next 5 CIS, remove from service IGHs that exhibit porosity levels in excess of the acceptable criteria listed in the SB and replace with serviceable parts. (6) Prior to further flight, remove from service cracked IGHs and LLB housings and replace with serviceable parts. (c) Inspect the master magnetic chip detector as follows: (1) Within 100 hours time in service (TIS) after the effective date of this AD, perform an initial inspection of the master magnetic chip detector in accordance with Mandatory SB No. RB.211-79-C093, Revision 1, February 28, 1997. (2) Thereafter, at intervals not less than 60 hours TIS and not greater than 130 hours TIS since last inspection, perform repetitive inspections of the master magnetic chip detector in accordance with Mandatory SB No. RB.211-79-C093, Revision 1, dated February 28, 1997. (d) 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, Engine Certification Office. The request should be forwarded through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Engine Certification Office. Note 2: Information concerning the existence of approved alternative methods of compliance with this airworthiness directive, if any, may be obtained from the EngineCertification Office. (e) 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 aircraft to a location where the inspection requirements of this AD can be accomplished. (f) The actions required by this AD shall be performed in accordance with the following R-R service documents: Document No. Pages Revision Date SB No. RB.211- 72-C089 1-3 1 January 24, 1997 Total pages: 3. SB No. RB.211- 72-C129 1-3 2 March 21, 1997 4-6 1 March 7, 1997 7 2 March 21, 1997 Total pages: 7. SB No. RB.211- 72-C114 1-48 Original February 6, 1997 Supplement 1-4 Original February 6, 1997 Total pages: 52. SB No. RB.211- 79-C093 1,2 1 February 28, 1997 Total pages: 2. 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 Rolls-Royce North America, Inc., 2001 South Tibbs Ave., Indianapolis, IN 46241; telephone (317) 230-3995, fax (317) 230-4743. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, MA; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment becomes effective on May 15, 1997.
82-26-04: 82-26-04 DORNIER: Amendment 39-4518. Applies to Model DO28D-1 (Serial Nos. 4036, 4037, 4050, 4055 through 4058, 4303, 4308 through 4318, 4321 through 4325, 4331 and 4332) airplanes, certificated in any category, when equipped with ARC PA-500A autopilot actuators. COMPLIANCE: Required as indicated, unless already accomplished. To prevent restriction of control movement due to jamming of the ARC PA-500A actuator gear train, accomplish the following: (a) Within the next 100 hours time-in-service after the effective date of this AD and thereafter at intervals not to exceed 100 hours time-in-service, inspect the ARC PA-500A actuator in accordance with Dornier Service Bulletin No. 1069-2820, dated May 27, 1980, which incorporates ARC Field Engineering Service Bulletin No. 181. Prior to further flight correct any unsafe condition noted by adjustment or replacement of parts as necessary. (b) Within 12 months after the effective date of this AD, modify the ARC Model PA-500A actuator(s) in accordance with Dornier Service Bulletin No. 1069-2820, dated May 27, 1980, which incorporates ARC Field Engineering Service Bulletin No. 181. (c) The inspections required by paragraph (a) of this AD may be discontinued when the modifications required in paragraph (b) of this AD have been accomplished. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) The intervals between repetitive inspections required by this AD may be adjusted up to 10 hours time-in-service to allow them to be accomplished concurrent with other scheduled maintenance on the airplane. (f) An equivalent method of compliance with this AD may be used if approved by the Manager, Aircraft Certification Staff, AEU-100, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, Brussels, Belgium. This amendment becomes effective on December 27, 1982.
97-15-13: This amendment adopts a new airworthiness directive (AD) that applies to certain Raytheon Aircraft Company (Raytheon) Models 1900, 1900C, and 1900D airplanes (formerly referred to as Beech Models 1900, 1900C, and 1900D airplanes). This action requires installing lubrication fittings in the airstair door handle and latch housing mechanisms. The AD results from reports of the airstair door not opening because the door was frozen shut. The actions specified by this AD are intended to prevent moisture from accumulating and freezing in the airstair door handle and latch housing, which could result in the door freezing shut and passengers not being able to evacuate the airplane in an emergency situation.
2007-01-09: The FAA is adopting a new airworthiness directive (AD) for certain Boeing Model 747-100B SUD, 747-200B, 747-300, 747-400, 747- 400D, and 747SP series airplanes. This AD requires repetitive inspections for cracking of the crease beam and adjacent intercostals, stringers, frames, and skin panels; and related investigative and corrective actions if cracking is found. This AD results from a report indicating that an operator discovered crease beam cracking on two Model 747 airplanes. We are issuing this AD to detect and correct cracking of the crease beam and adjacent structure, which could become large and result in in-flight depressurization and inability of the airframe structure to sustain flight loads.
2007-02-11: We are adopting a new airworthiness directive (AD) to supersede AD 2002-21-11, which applies to certain EXTRA Flugzeugbau GmbH (EXTRA) Model EA-300S airplanes. AD 2002-21-11 currently requires you to inspect, using a fluorescent dye check penetrant method, the upper longeron at the horizontal stabilizer attachment for cracks, repair any cracks found, and modify the horizontal stabilizer. That AD also requires a limit on operation to the Normal category until the initial inspection and modification on airplanes with less than 200 hours time-in-service is done. Since we issued AD 2002-21-11, cracks have been found on Models EA-300L and EA-300/200 airplanes. Consequently, this AD adds airplanes to the Applicability section and requires you to inspect and modify the upper longeron at the horizontal stabilizer attachment. This AD results from mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. We are issuing this AD to detect, correct, and prevent cracks in the upper longeron at the horizontal stabilizer attachment, which could result in structural failure of the aft fuselage. This failure could lead to loss of control.
84-08-05 R1: 84-08-05 R1 BOEING: Amendment 39-4852 as amended by Amendment 39-4889. Applies to Boeing Model 727-100 airplanes modified to install a Performance Data Computer under STC SA1602NM. To preclude the loss of airspeed information due to conditions related to the pitot- static system, accomplish the following no later than November 5, 1984, unless already accomplished. \n\n\tA)\tConnect the first and second pilots' flight instruments to the appropriate pitot-static systems to conform with Civil Air Regulations (CAR) 4b.612 using a means approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tB)\tPerform a leak check of the pitot-static system in accordance with Federal Aviation Regulations (FAR) Part 91.170. \n\n\tC)\tPerform a functional test of the air data system. \n\n\tD)\tPerform a functional check of the pitot heat system. \n\n\tE)\tAlternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region.\n \n\tAmendment 39-4852 became effective May 7, 1984. \n\tThis Amendment 39-4889 becomes effective August 1, 1984.
2019-14-01: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) TAY 650-15 and TAY 651-54 turbofan engines with low-pressure compressor (LPC) fan blade module M01300AA or M01300AB, installed. This AD was prompted by reports of LPC fan blade retention lug fractures on engines with a high number of dry- film lubrication (DFL) treatments. This AD requires determining the number of DFL treatments applied on each LPC fan blade, and removing from service and replacing the affected LPC fan blades if the DFL treatment limit is exceeded. The FAA is issuing this AD to address the unsafe condition on these products.