Results
2012-13-10: We are adopting a new airworthiness directive (AD) for the PZL Swidnik S.A. (PZL) Model PZL W-3A helicopter with a certain generator air outlet collector (collector) installed. This AD requires modifying the generator air outlet collector attachments (collector attachments). This AD is prompted by an incident where cyclic control stick movement was restricted due to rotation of a loose collector, resulting in locking of the longitudinal control system hydraulic actuator fork end. These actions are intended to prevent rotation of the collector, which could lead to restricted cyclic control stick movement, and subsequent loss of control of the helicopter.
99-06-02: This amendment adopts a new airworthiness directive (AD) that applies to certain Fairchild Aircraft, Inc. (Fairchild) SA226 and SA227 series airplanes. This AD requires repetitively inspecting the wing spar center web cutout on both wings for cracks between Wing Station (WS) 8 and WS 17.5, and immediately repairing any area found cracked. This repair will eliminate the need for the repetitive inspections on that particular wing spar. This AD is the result of reports of cracks in the wing spar center web cutout caused by fatigue due to airplane maneuvering and wind gusts. The actions specified by this AD are intended to detect and correct fatigue cracking of the wing spar center web cutout area, which could result in structural failure of the wing spar to the point of failure with consequent loss of control of the airplane.
2003-08-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Bombardier Model CL-600-1A11 (CL-600), CL-600-2A12 (CL-601), and CL-600-2B16 (CL-601-3A, CL-601-3R, and CL-604) series airplanes. This action requires a detailed inspection to detect cracks of the vane brackets of the inboard flap actuator beam, and follow-on repetitive detailed inspections or corrective actions, as applicable. This action also provides for two optional terminating actions for the detailed inspection(s). This action is necessary to detect and correct gaps between the flap vane bracket and the adjacent lower skin and between the flap vane bracket and vane actuator beam of the wing flap systems, and premature cracking of the flap vane brackets, which could result in failure of the flap vane bracket(s) when the flaps are extended and the flap vane is aerodynamically loaded. Loss or warping of the flap vane in flight could decrease the lift on one side of the airplane, which could lead to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
67-32-01: 67-32-01 BRITISH AIRCRAFT CORP: Amendment 39-573. Applies to BAC 1-11 Airplanes Model/Type 212AR, 401AK, 410AQ, which have a center fuel tank fitted with Thompson Ramo fuel pumps P/N 248800/4, P/N 248800/5 or pumps manufactured under license by Plessey which include additional part number 570/1/21221/004. Amendment 39-522 (32 F.R. 17515), AD 67-32-1, is amended. Compliance required as indicated. To prevent fuel pump movement and consequent fuel leakage, accomplish the following: (a) Within the next 200 hours' time in service after the effective date of this AD, unless already accomplished, inspect the center tank fuel pump installation in accordance with BAC 1-11 Alert Service Bulletin 28-A-PM 2701, Issue 2, or later ARB-approved issue, or FAA- approved equivalent. (b) If leaks are found when conducting the inspection required by paragraph (a), before further flight stop the leaks by repositioning the fuel booster pump and, if necessary, replacing the seals between the pump and canister. (c) Within the next 1,000 hours' time in service after the effective date of this AD, modify the center tank fuel booster pumps in accordance with British Aircraft Corporation Service Bulletin No. 28-PM 2701 or later ARB-approved issue, or an equivalent approved by the Chief, Aircraft Certification Staff, European Region. This amendment becomes effective May 2, 1968.
2012-13-12: We are adopting a new airworthiness directive (AD) for certain Gulfstream Aerospace Corporation Model G-IV, GIV-X, GV, and GV-SP airplanes. This AD requires measuring to determine paint thickness on the flight control surfaces and corrective actions if necessary, and revising the Airplane Flight Manual (AFM). This AD was prompted by reports of failure to inspect or document the paint thickness on flight controls (ailerons, rudder, elevator), potentially having a negative impact on the flutter characteristics of the airplane. We are issuing this AD to detect and correct paint thickness on flight controls, which could result in loss of control of the airplane due to flutter.
99-06-18: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400, -400D, and -400F series airplanes, that requires modification of the P212 and P213 panels of the cabin pressure control system. For certain airplanes, this amendment also requires modification of the P5, P6, and P7 panels, and the W4701, W4703, and W4908 wire bundles, as applicable. This amendment is prompted by a report of in-flight loss of cabin pressurization control due to a single failure of the auxiliary power unit (APU) battery. The actions specified by this AD are intended to prevent loss of control of the cabin pressurization system, which could result in rapid depressurization of the airplane. Such rapid depressurization could result in deleterious physiological effects on the passengers and crew; and airplane diversions, which represent an increased risk to the airplane, passengers, and crew.
2012-13-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, -300ER, and 777F series airplanes. This AD was prompted by a report indicating that a fire originated near the first officer's area, which caused extensive damage to the flight deck. This AD requires replacing the low-pressure oxygen hoses with non-conductive low-pressure oxygen hoses in the flight compartment. We are issuing this AD to prevent electrical current from passing through the low-pressure oxygen hose internal anti-collapse spring, which can cause the low-pressure oxygen hose to melt or burn, and a consequent oxygen-fed fire in the flight compartment.
55-15-02: 55-15-02 CONVAIR: Applies to All 240 and 340 Series Aircraft Equipped with Hamilton Standard Propellers. Compliance required by first scheduled engine change after November 1, 1955, but not later than November 1, 1956. To increase the fire resistance integrity of the propeller feathering system against damage by a powerplant fire, all flexible hose components of propeller feathering lines forward of the firewall in zone 2 must be replaced with lines and fittings which will meet current fire resistance requirements. Convair Service AirGram No. 123 dated October 8, 1954, covers this subject. The following hose assemblies may also be considered acceptable for this application: (a) Aeroquip 680-10S hose assemblies with Aeroquip 304 protective sleeves over end fittings (Aeroquip assembly P/N 304000). (b) Resistoflex-SSFR-3800-10 hose assemblies. (c) Aeroquip 309009 hose assemblies.
2018-04-12: We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737-100, -200, -200C, -300, -400, -500 series airplanes. This AD was prompted by a report of wire damage on a fuel boost pump power cable, and a separate report of a fuel tank explosion on a similarly equipped airplane. This AD requires the installation of new shielded wire bundles and convoluted liners within fuel tank conduits, and revision of the maintenance or inspection program, as applicable, to incorporate certain airworthiness limitations (AWLs). We are issuing this AD to address the unsafe condition on these products.
2012-14-06: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Corporation (RRC) 250-C20, -C20B, and -C20R/2 turboshaft engines. This AD was prompted by seven cases reported of released turbine blades and shrouds, which led to loss of power and engine in- flight shutdowns (IFSDs). This AD requires a one-time visual inspection and fluorescent penetrant inspection (FPI) on certain 3rd and 4th stage turbine wheels for cracks in the turbine blades. We are issuing this AD to prevent failure of 3rd or 4th stage turbine wheel blades which could cause engine failure and damage to the airplane.
2003-08-11: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 747-100, -200B, -200F, -200C, -100B, -300, -100B SUD, -400, -400D, and -400F series airplanes; and Model 747SR series airplanes. This action requires repetitive inspections to detect discrepancies of the actuator attach fittings of the inboard and outboard flaps, and follow-on and corrective actions as necessary. This action is necessary to detect and correct cracking and other damage of the actuator attach fittings of the trailing edge flaps, which could result in abnormal operation or retraction of a trailing edge flap, and possible loss of controllability of the airplane. This action is intended to address the identified unsafe condition.
96-17-14: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4 series airplanes, that currently requires repetitive visual inspections to detect cracks in the forward intermediate section skin at frame 30A where it joins stringer 30, and repair, if necessary. This amendment adds a requirement for eddy current inspection(s) to detect cracks of the outer skin of the fuselage; accomplishment of this inspection terminates the repetitive visual inspections. This amendment also requires repair of any cracked area and modification of the structure at certain frames. This amendment is prompted by in-service experience which has identified fatigue cracks in this area. The actions specified by this AD are intended to prevent fatigue cracking, which could result in rapid decompression of the airplane.
2018-04-11: We are adopting a new airworthiness directive (AD) for Agusta S.p.A. Model AB139 and Model AW139 helicopters. This AD requires inspecting the thickness of the tail gearbox (TGB) central housing (housing). This AD was prompted by reports that the housing thickness does not conform to its type design. The actions of this AD are intended to detect and correct an unsafe condition on these products.
99-05-10: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 757 series airplanes, that requires revising the maintenance program to require verification that a certain shipping container and shipping sleeve assembly were used in shipping the ram air turbine (RAT) deployment actuator. This amendment also requires inspection of the identification plate on the RAT deployment actuator to determine the actuator serial numbers or a records check to determine such information; and repair or replacement of certain RAT deployment actuators, if necessary. This amendment is prompted by reports of certain RAT actuators that failed to deploy upon command due to interference in the actuator locking mechanism caused by damage incurred during shipping of the actuators. Failure of the RAT to deploy, specifically during a dual engine failure, would result in loss of hydraulic power and would adversely affect the continued safe flight and landing of the airplane.
99-05-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-100, -200, -300, -400, and -500 series airplanes. This action requires removal of the float switch and wiring and inspection of the float switch wiring in the center fuel tank to detect discrepancies, and either reinstallation of existing float switch and wiring, or replacement of the float switch and wiring with a new float switch and wiring. This action also requires installation of Teflon sleeving over the wiring of the float switch. In lieu of the above mentioned requirements, this AD requires deactivation of the float switch, accomplishment of specific fueling procedures, and installation of Caution signs. This amendment is prompted by a report indicating that chafing of the direct current (DC) powered float switch wiring insulation in the center fuel tank has occurred on several airplanes. The actions specified in this AD are intended to detect and correct suchchafing and the resultant arcing from the wiring to the in-tank conduit, which could present an ignition source inside the fuel tank and consequent fire/explosion.
99-05-08: This amendment adopts a new airworthiness directive (AD) that is applicable to McDonnell Douglas Helicopter Systems (MDHS) Model MD-900 helicopters. This action requires establishing or reducing certain life limits, applying serial numbers (S/N's), determining hours time-in-service (TIS), and creating component history cards or equivalent records for various parts. This amendment is prompted by analysis that indicates a need for establishing or reducing life limits to avoid fatigue failure of certain parts. The actions specified by this AD are intended to apply appropriate life limits to various parts.
93-01-26: 93-01-26 DE HAVILLAND, INC.: Amendment 39-8480. Docket 92-NM-99-AD. Supersedes AD 91-19-04, Amendment 39-8031 which superseded AD 91-12-51, Amendment 39-7076. Applicability: Model DHC-8-300 series airplanes; serial numbers 202, 210, 216, 221, 224, 230, 232, 234, 236, 238, 240, 242, 244, 246, 248, 250, 252, 254, 256, 257, 259, 261, 262, 264, 266, 267, 269, 271, 272, 274, 276, 278, 279, 281, 283, 284, 286, 288, and 307; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent the accumulation of fuel vapors in the dry bay area, presenting a potential risk of an in-flight explosion in the event of a lightning strike, accomplish the following: (a) For those airplanes listed in de Havilland Alert Service Bulletin S.B. A8-28-16, dated May 30, 1991, accomplish the following: (1) Within 24 hours after August 26, 1991 (the effective date of AD 91-12- 51, Amendment 39-7076), and thereafter at intervals not to exceed 300 hours time-in-service or 30 days, whichever occurs first, perform an external visual inspection of the wing dry bay drains for blockage in accordance with the service bulletin. If drain blockage is found, prior to further flight, repair in accordance with paragraph B.1. of the Accomplishment Instructions of the service bulletin. (2) Within 24 hours after August 26, 1991, and thereafter at daily intervals, perform an external visual inspection of the wing dry bay drains to detect evidence of fuel leaks in accordance with the service bulletin. (3) Within 7 days after August 26, 1991, unless accomplished within the previous 14 days; or prior to further flight if evidence of fuel leaks is detected at the wing dry bay drains as a result of the inspection required by paragraph (a)(2) of this AD; perform an internal visual inspection of the wing dry bay in accordance with the service bulletin. (i) If no leakage is found as a result of the inspection required by paragraph (a)(3) of this AD, repeat the internal visual inspection of the wing dry bay required by paragraph (a)(3) of this AD at intervals not to exceed 14 days. (ii) If the leakage is within the limits specified in the service bulletin, within 14 days, perform the local re-sealing repair procedure described in paragraph C.7. of the Accomplishment Instructions of the service bulletin. The airplane may be returned to service within this 14-day period, subject to the following conditions: (A) Perform the internal visual inspection of the wing dry bay required by paragraph (a)(3) of this AD at intervals not to exceed 7 days to ensure that the leakage remains within the specified limit; and (B) Prior to further flight, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM), which may be accomplished by including a copy of this airworthiness directive in the AFM: "Flight is prohibited in areas where lightning or thunderstorms are observed or reported within 5 nautical miles of the flight path, or when the existing weather conditions may reasonably be expected to result in a lightning strike." (iii) If leakage exceeds the limit specified in the service bulletin, prior to further flight, repair in accordance with paragraph C.7. of the Accomplishment Instructions of the service bulletin. (iv) Application of a fuel vapor barrier coating in accordance with paragraph D. of the Accomplishment Instructions of the service bulletin constitutes terminating action only for the repetitive internal visual inspections required by paragraph (a)(3)(i) of this AD. (b) For those airplanes listed in de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'B', dated June 24, 1991, that are not subject to paragraph (a) of this AD, accomplish the following: (1) Within 24 hours after September 26, 1991 (the effective date of AD 91- 19-04, Amendment 39-8031), and thereafter at intervals not to exceed 300hours time-in-service or 30 days, whichever occurs first, perform an external visual inspection of the wing dry bay drains for blockage in accordance with the service bulletin. If drain blockage is found, prior to further flight, repair in accordance with paragraph B.1. of the Accomplishment Instructions of the service bulletin. (2) Within 24 hours after September 26, 1991, and thereafter at daily intervals, perform an external visual inspection of the wing dry bay drains to detect evidence of fuel leaks in accordance with the service bulletin. (3) Within 7 days after September 26, 1991, unless accomplished within the previous 14 days; or prior to further flight if evidence of fuel leaks is detected at the wing dry bay drains as a result of the inspection required by paragraph (b)(2) of this AD; perform an internal visual inspection of the wing dry bay in accordance with the service bulletin. (i) If no leakage is found as a result of the inspection required by paragraph (b)(3) of this AD, repeat the internal visual inspection of the wing dry bay required by paragraph (b)(3) of this AD at intervals not to exceed 14 days. (ii) If the leakage is within the limits specified in the service bulletin, within 14 days, perform the local re-sealing repair procedure described in paragraph C.7. of the Accomplishment Instructions of the service bulletin. The airplane may be returned to service within this 14-day period, subject to the following conditions: (A) Perform the internal visual inspection of the wing dry bay required by paragraph (b)(3) of this AD at intervals not to exceed 7 days to ensure that the leakage remains within the specified limit; and (B) Prior to further flight, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM), which may be accomplished by including a copy of this airworthiness directive in the AFM: "Flight is prohibited in areas where lightning or thunderstorms are observed or reported within 5 nautical miles of the flight path, or when the existing weather conditions may reasonably be expected to result in a lightning strike." (iii) If leakage exceeds the limit specified in the service bulletin, prior to further flight, repair in accordance with paragraph C.7. of the Accomplishment Instructions of the service bulletin. (iv) Application of a fuel vapor barrier coating in accordance with paragraph D. of the Accomplishment Instructions of the service bulletin constitutes terminating action only for the repetitive internal visual inspections required by paragraph (b)(3)(i) of this AD. (c) For airplane serial numbers 279, 281, 283, 284, 286, 288, and 307, accomplish the following in accordance with de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'C', dated January 31, 1992: (1) Within 7 days after the effective date of this AD, and thereafter at intervals not to exceed 300 hours time-in-service or 30 days, whichever occurs first, perform an external visual inspection of the wing dry bay drains for blockage in accordance with the service bulletin. If drain blockage is found, prior to further flight, repair in accordance with paragraph B.1. of the Accomplishment Instructions of the service bulletin. (2) Within 7 days after the effective date of this AD, and thereafter at daily intervals, perform an external visual inspection of the wing dry bay drains to detect evidence of fuel leaks in accordance with the service bulletin. (3) Within 7 days after the effective date of this AD, unless accomplished within the previous 14 days; or prior to further flight if evidence of fuel leaks is detected at the wing dry bay drains as a result of the inspection required by paragraph (c)(2) of this AD; perform an internal visual inspection of the wing dry bay in accordance with the service bulletin. (i) If no leakage is found as a result of the inspection required by paragraph (c)(3) of this AD, repeat the internal visual inspection of the wing dry bay required by paragraph (c)(3) of this AD at intervals not to exceed 14 days. (ii) If the leakage is within the limits specified in the service bulletin, within 14 days, perform the local re-sealing repair procedure described in paragraph C.7. of the Accomplishment Instructions of the service bulletin. The airplane may be returned to service within this 14-day period, subject to the following conditions: (A) Perform the internal visual inspection of the wing dry bay required by paragraph (c)(3) of this AD at intervals not to exceed 7 days to ensure that the leakage remains within the specified limit; and (B) Prior to further flight, incorporate the following into the Limitations Section of the Airplane Flight Manual (AFM), which may be accomplished by including a copy of this airworthiness directive in the AFM: "Flight is prohibited in areas where lightning or thunderstorms are observed or reported within 5 nautical miles of the flight path, or when the existing weather conditions may reasonably be expected to result in a lightning strike." (iii) If leakage exceeds the limit specified in the service bulletin, prior to further flight, repair in accordance with paragraph C.7. of the Accomplishment Instructions of the service bulletin. (iv) Application of a fuel vapor barrier coating in accordance with paragraph D. of the Accomplishment Instructions of the service bulletin constitutes terminating action only for the repetitive internal visual inspections required by paragraph (c)(3)(i) of this AD. (d) Within 6 months after the effective date of this AD, accomplish Modification No. 8/1776 in accordance with de Havilland Service Bulletin S.B. 8-57-20, Revision A, dated January 31, 1992. Accomplishment of this modification constitutes terminating action for the requirements of this AD. (e) 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, New York Aircraft Certification Office (ACO), ANE-170, FAA, Engine and Propeller Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, New York ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the New York ACO. (f) 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. (g) Certain inspections, repairs, and modification shall be done in accordance with de Havilland Alert Service Bulletin S.B. A8-28-16, dated May 30, 1991; de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'C', dated January 31, 1992; and de Havilland Service Bulletin S.B. 8-57-20, Revision 'A', dated January 31, 1992; as indicated. 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. Certain other inspections, repairs, and modifications shall be done in accordance with de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'B', dated June 24, 1991. Incorporation by reference of de Havilland Alert Service Bulletin S.B. A8-28-16, Revision 'B', dated June 24, 1991, was approved previously by the Director of the Federal Register as of September 26, 1991 (56 FR 46228, September 11, 1991). Copies may be obtained from de Havilland, Inc., Garratt Boulevard, Downsview, Ontario M3K 1Y5, Canada. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, New York Aircraft Certification Office, 181 South Franklin Avenue, Valley Stream, New York; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington,DC. (h) This amendment becomes effective on March 10, 1993.
2003-04-17: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and MD-11F airplanes, that requires an inspection to detect damage of the wiring/bundles routed to the wire support bar of the circuit breaker panel and to the circuit breakers, and an inspection of the wiring/bundles for correct routing. This amendment also requires installation of protective sleeving, spacers, and sta-straps; and corrective/follow-on actions, if necessary. The actions specified by this AD are necessary to prevent chafing and consequent arcing or loss of electrical power to associated avionics buses in the upper avionics circuit breaker panel of the main observer's station, which could result in smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
73-23-07: 73-23-07 CESSNA: Amdt. 39-1744. Applies to Model 150 (S/Ns 15074635 thru 15074799); Model A150 (S/Ns A1500415 thru 1500427); Model 172 (S/Ns 17261664 thru 17261808); Model 180 (S/Ns 18052335 thru 18052349); Model 182 (S/Ns 18261960 thru 18262105) and Model 185 (S/Ns 18502199 thru 18502238) airplanes. Compliance: Required as indicted, unless already accomplished. To prevent defective spar attachment fitting from remaining in service, within the next 50 hours' time in service after the effective date of this AD, replace P/N 0523306 wing attach fittings with Cessna Service Kit SK 150-45A, dated July 27, 1973, referred to in Cessna Service Letter SE73-20, dated August 17, 1973, or later FAA-approved revisions, or with any other airworthy part approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. This amendment becomes effective November 19, 1973.
2003-08-08: This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes, that currently requires, among other actions, a one-time inspection to detect discrepancies at certain areas around the entry light connector of the sliding ceiling panel above the forward passenger doors; repair, if necessary; and installation or modification of a flapper door ramp deflector on the forward entry drop ceiling structure. That AD also currently requires an inspection of the wire assembly support installation above the entry door (L1) sliding panel for chafing, and repair, if necessary. This amendment requires the existing requirements and requires replacing the wire support bracket with new support clip assemblies. The actions specified by this AD are intended to prevent chafing of electrical wire assemblies above the forward passenger doors and above the entry door (L1) sliding panel of the forward drop ceiling on the passenger compartment, which could result in electrical arcing, and consequent electrical fire in the passenger compartment. This action is intended to address the identified unsafe condition.
99-05-05: This amendment adopts a new airworthiness directive (AD), applicable to International Aero Engines AG (IAE) V2500-A1 series turbofan engines, that requires initial and repetitive inspections of certain High Pressure Turbine (HPT) stage 1 and stage 2 disks utilizing an improved ultrasonic method when the disks are exposed during a normal shop visit, and if a subsurface anomaly is found, removal from service and replacement with a serviceable part. This amendment is prompted by the results of a stage 1 HPT disk fracture investigation which has identified a population of HPT stage 1 and 2 disks that may have subsurface anomalies formed as a result of the processes used to manufacture the material. The actions specified by this AD are intended to prevent HPT disk fracture, which could result in an uncontained engine failure, and damage to the airplane.
99-04-19: This amendment adopts a new airworthiness directive (AD) that is applicable to all Boeing Model 777 series airplanes. This action requires repetitive detailed visual inspections to detect cracking of the cove skin on the outboard leading edge slats; a slat adjustment check; and corrective actions, if necessary. This amendment is prompted by reports of fatigue cracking and/or missing pieces of the cove skin on the outboard leading edge slats. The actions specified in this AD are intended to detect and correct such discrepancies, which could result in skin separation or structural damage to the leading edge slats, and consequent reduced controllability of the airplane.
2012-11-14: We are adopting a new airworthiness directive (AD) for all Pratt & Whitney Canada (P&WC) PW118, PW118A, PW118B, PW119B, PW119C, PW120, PW120A, PW121, PW121A, PW123, PW123B, PW123C, PW123D, PW123E, PW123AF, PW124B, PW125B, PW126A, PW127, PW127E, PW127F, PW127G, and PW127M turboprop engines. This AD requires initial and repetitive inspections of certain serial numbers (S/Ns) of propeller shafts for cracks and removal from service if found cracked. This AD was prompted by reports of two propeller shafts found cracked at time of inspection during maintenance. We are issuing this AD to detect propeller shaft cracks, which could cause failure of the shaft, propeller release, and loss of control of the airplane.
74-16-04: 74-16-04 BEECH: Amendment 39-1908. Applies to Models 65-B80 (Serial Numbers LD-452 through LD-468), C90 (Serial Numbers LJ-552 through LJ-588) and E90 (Serial Numbers LW-1 through LW-56) airplanes. \n\n\tCompliance: Required as indicated, unless already accomplished. \n\n\tTo prevent restricted elevator travel, within the next 100 hours' time in service after the effective date of this AD, accomplish the following: \n\n\tInstall a MS20365-428 self-locking nut on the threaded portion of each of the four elevator control stop bolts in accordance with the attached sketch and Part I of Beechcraft Service Instruction 0618-152 or subsequent revisions or by any equivalent method of compliance approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. \n\n\tThis amendment becomes effective August 6, 1974.
99-04-23: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737 series airplanes, that requires repetitive ultrasonic inspections to detect broken bolts that attach the terminal support fittings to the upper part of the Body Station 1088 bulkhead, and corrective actions, if necessary. This amendment also requires eventual replacement of the existing bolts with new, improved bolts, which, when accomplished, terminates the repetitive inspection requirements of this AD. This amendment is prompted by reports that bolts that attach the terminal support fittings to the upper part of the bulkhead were found broken. The actions specified by this AD are intended to prevent such broken bolts, which could result in reduced structural integrity of the vertical fin installation and possible loss of the vertical fin.