Results
98-20-37: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200, and -300 series airplanes, that requires the replacement of certain switches located in the cabin attendant's panel at doors 1 and 3 right with new, improved switches. This amendment is prompted by reports indicating that fires have occurred on some airplanes due to the internal failure of some of these switches. The actions specified by this AD are intended to prevent the installation and use of such switches that could short circuit when they fail, and consequently cause fire and smoke aboard the airplane.
91-18-10: 91-18-10 BOEING: Amendment 39-8013. Docket No. 90-NM-206-AD. \n\n\tApplicability: Model 767 series airplanes equipped with brake part numbers (P/N) identified in paragraph (a) of this AD, certificated in any category. \n\n\tCompliance: Required as indicated, unless previously accomplished. \n\n\tTo prevent the loss of main landing gear braking effectiveness, accomplish the following: \n\n\t(a)\tWithin 180 days after the effective date of this AD, incorporate the maximum brake wear limits, shown below, into the FAA-approved maintenance inspection program. \n\nBrake Mfr. \tBrake P/N\t Boeing P/N\t Max. Wear Limit \n\nBendix\t\n2607092-1\t\nS160T200-12\t\n2.15 inches \nBendix\t\n2607092-2\nS160T200-13\n2.15 inches \nBendix\t\n2607092-3\t\nS160T200-14\n2.15 inches \nBendix\t\n2607092-4\nS160T200-15\n2.15 inches \nBendix\t\n2608812-4\t\nS160T300-12\n2.56 inches \nBendix\t\n2608812-6\t\nS160T300-14\n2.90 inches \n\t\n\t(b)\tAn alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Seattle ACO. \n\n\t(c)\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. \n\n\tThis amendment (39-8013, AD 91-18-10) becomes effective on November 12, 1991.
90-05-10: 90-05-10 SAAB-SCANIA: Amendment 39-6530. Docket No. 90-NM-19-AD. Applicability: Model SF-340A series airplanes, Serial Numbers 004 through 159; and SAAB 340B series airplanes, Serial Numbers 160 through 166; certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent the loss of structural integrity of the powerplant installation, accomplish the following: A. Within 50 hours time-in-service after the effective date of this AD, inspect the drag strut bolts, lower fittings, and attaching bolts to verify the type of nuts/collars installed, in accordance with SAAB Service Bulletin 340-54-026, dated December 1, 1989. 1. If the inboard and outboard lower drag strut support fittings have been installed with Hi-Lock pins and MS nuts, Part No. MS21042L3, no further action is required. 2. If the inboard and outboard lower drag strut support fittings have not been installed with MS21042L3 nuts, prior to further flight, accomplish the following: a. Remove the seven collars at the lower drag strut support fitting, in accordance with Figure 1 of the service bulletin. b. Perform a visual inspection for defects around the hole edges. If defects are found, repair prior to further flight, in a manner approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. c. Install MS21042L3 nuts, and AN960KD10 or AN960KD10L washers, in accordance with paragraph 2.B.(4) of the service bulletin. B. 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. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who will either concur or comment and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issuedin accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to SAAB-Scania, Product Support, S- 581.88, Linkoping, Sweden. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Standardization Branch, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6530, AD 90-05-10) becomes effective on March 21, 1990.
2013-05-17: We are adopting a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-61A, D, E, L, N, NM, R, and V helicopters to require replacing each forward and aft fuel system 40 micron fuel filter element with a 10 micron nominal (40 micron absolute) fuel filter element. This AD was prompted by a National Transportation Safety Board (NTSB) review of in-service events where engine performance degradation occurred, and the review determined that some of these events were caused by contaminants larger than 10 microns present in the engine fuel control units (FCUs). The actions are intended to prevent particulate contamination in the FCU, which could lead to malfunction of an internal valve, power loss at a critical phase of flight, and loss of control of the helicopter.
96-12-03 R2: This amendment revises Airworthiness Directive (AD) 96-12-03 R1, which applies to Aviat Aircraft, Inc. (Aviat) Models S-1S, S-1T, S-2, S-2A, S-2S, and S-2B airplanes that are equipped with aft lower fuselage wing attach fittings incorporating part number (P/N) 76090, P/N 2-2107-1, or P/N 1-210-102. AD 96-12-03 R1 currently requires repetitively inspecting the aft lower fuselage wing attach fitting on both wings for cracks, and modifying any cracked aft lower fuselage wing attach fitting. Modifying both aft lower fuselage wing attach fittings eliminates the repetitive inspection requirement of AD 96-12-03. Aviat started incorporating modified aft lower fuselage wing attach fittings on newly manufactured airplanes beginning with serial number 5337, instead of 5349 as referenced in the existing AD. This AD retains the repetitive inspection and possible modification requirements of AD 96-12-03 R1, and will change the applicability accordingly. The actions specified by this AD are intended to prevent possible in-flight separation of the wing from the airplane caused by a cracked fuselage wing attach fitting.
60-20-04: 60-20-04 LOCKHEED: Amdt. 203 Part 507 Federal Register September 28, 1960. Applies to 188 Aircraft Serial Numbers 1002, 1004 Through 1102, 1104 Through 1126, and 2001 Through 2015. Compliance required by the next 300 hours' time in service after October 28, 1960. Leaking lavatory tank ground drain valves have permitted drainage to the exterior surface of the aircraft in flight, resulting in ice formation which came off and struck the stabilizer. Since such ice formation is hazardous to aircraft in flight and to persons on the ground, all lavatory tank ground drain valves must be modified to incorporate LAC seal No. 838228-1 or equivalent. (LAC 88/SB-407 covers the intent of this change.) This directive effective October 28, 1960.
88-25-09: 88-25-09 AEROSPATIALE (SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE): Amendment 39-6237. Final copy of priority letter AD. (Docket No. 88- ASW-59) Applicability: All Aerospatiale Model AS 355 series helicopters containing Part Number (P/N) 355A34-1037-00, tail rotor drive shaft, certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent tail rotor drive shaft failure, which could result in the loss of control, accomplish the following: (a) Within the next 50 hours' time in service after receipt of this AD, and thereafter at intervals not to exceed 100 hours' time in service, perform the vibration level measurement with the aircraft on the ground and with the rotor turning, in accordance with Maintenance Work Card 65-10-00-604. (1) If the measured vibration level is equal to or above 3 inches per second (IPS)-- (i) Replace the tail rotor drive shaft with a serviceable part prior to further flight; or(ii) The tail rotor drive shaft may be operated for no more than an additional 50 hours' time in service provided the vibration level is reduced to 1.75 IPS or below, and no cracks are found by the following inspections. Before the next flight and thereafter at intervals not to exceed 10 hours' time in service, inspect the inside surface of the shaft in the area of the forward flange and splined fitting attachment (both ends of the shaft, adjacent to the Jo- bolts) for cracks. If cracks are found, replace the tail rotor drive shaft with an airworthy shaft prior to further flight. (2) If the measured vibration level is above 1.75 IPS, but less than 3 IPS: (i) Clean the fan assembly in accordance with Maintenance Work Card 12-00-00-306. (ii) Perform a new vibration level check. (iii) If the vibration level is less than 1.75 IPS after cleaning, no further action is required. (iv) If the vibration level is above 1.75 IPS, balance the fan assemblyin accordance with Maintenance Work Card 65-10-00-604, and perform a new vibration level check. (A) If the vibration level is less then 1.75 IPS after balancing, no further action is required. (B) If the measured vibration level measures above 1.75 IPS, inspect the sliding flange splines for wear and the fan bearings for abnormal play in accordance with the applicable Maintenance Work Cards. Replace parts found outside specified limits and perform a new vibration check. If the vibration level remains above 1.75 IPS, replace the tail rotor drive shaft with a serviceable part prior to further flight. (3) If the measured vibration level is below 1.75 IPS, no further action is required. (b) Accomplish the vibration level measurement and shaft replacement, as necessary, in accordance with the instruction of paragraph (a) before and after the replacement of any fan assembly component or any tail rotor drive shaft. (c) Replace the tail rotor drive shaft in accordance with the instructions of paragraph (a)(1) if-- (1) The vibration level exceeded 3 IPS as measured during previous compliance with Aerospatiale Service Bulletin 05.20, before issuance of this AD; or (2) The tail rotor drive shaft was installed when the oil cooler fan was changed for foreign object damage or when the fan bearings were changed for bearing discrepancies. (d) An alternate method of compliance with the AD which provides an equivalent level of safety may be used if approved by the Manager, Rotorcraft Standards Staff, ASW-110, FAA, Fort Worth, Texas 76193-0110. This amendment (39-6237, AD 88-25-09) becomes effective on July 14, 1989, as to all persons except those persons to whom it was made immediately effective by priority letter AD No. 88-25-09, issued December 9, 1988, which contained this amendment.
2013-05-05: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 777-200, -200LR, -300, and -300ER series airplanes. This AD was prompted by reports of in-service events related to electrical power system malfunctions resulting in damage to electrical load management system (ELMS) P200 and P300 power panels and the surrounding area. This AD requires installing enclosure trays to contain debris in certain ELMS panels, and replacing certain ELMS contactors. We are issuing this AD to prevent contactor failures, which could result in uncontained hot debris flow due to ELMS contactor breakdown, consequent smoke and heat damage to airplane structure and equipment during ground operations, and possible injuries to passengers and crew.
98-20-40: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-100, -200, -300, SP, and SR series airplanes, that requires the installation of shielding and separation of the electrical wiring of the fuel quantity indication system (FQIS). This amendment is prompted by a failure analysis of the FQIS, and by testing results, which revealed that excessive energy levels in the electrical wiring and probes of the fuel system could be induced by electrical transients. The actions specified by this AD are intended to prevent electrical transients, induced by electromagnetic interference (EMI), or electrical short circuit conditions from causing arcing of the FQIS electrical wiring or probes in the fuel tank(s). Such arcing could result in ignition of the fuel tank(s).
89-01-01: 89-01-01 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE (SNIAS): Amendment 39-6052. Applicability: All SNIAS Model AS 355E, AS 355F, and AS 355F1 helicopters (serial numbers before 5362) fitted with debris guards, Part Numbers (P/N) 355A58-0519-0201 and 355A58-0519-0391, certificated in any category, except those helicopters previously equipped with this identical modification. (Docket No. 87-ASW-62) Compliance: Required within the next 200 hours' time in service, unless already accomplished. To prevent engine failure (flameout) resulting from ingestion of atmospheric moisture in engine inlets, accomplish the following: (a) Install an engine automatic relight system in accordance with SNIAS Service Bulletin AS 355 No. 80.02, Revision 2, approved July 8, 1987 (SB No. 80.02 corresponds to SNIAS Modification AMS 350A07-1823, IFR-VFR versions; AMS 350A07-1856, IFR versions; AMS 350A07-1905, IFR-VFR versions; AMS 350A07-1910, IFR-VFR versions; AMS 350A07- 1920, IFR-VFR version). Installation of the SNIAS relighting kit requires exclusive utilization of Champion or Auburn igniter P/N 6877518 or Champion igniter P/N 23006266 and limits the service life of each newly installed igniter to 1,200 hours' time in service. Any of the required Champion or Auburn igniters already installed and having 1,000 or more hours' time in service must be replaced with new Champion or Auburn P/N 6877518 igniters or Champion P/N 23006266 igniters. NOTE: SNIAS Service Bulletin AS 355 No. 01.18, Revision 2, approved October 5, 1987, also pertains to this engine automatic relight system installation. (b) Incorporate into the applicable RFM the basic flight manual revisions and instrument flight rules (IFR) flight manual supplements (if IFR equipped), or later FAA-approved flight manual revisions, as follows: (1) For the Model AS 355E, basic rotorcraft flight manual, Revision 4, Code Date 87-10. (2) For the Model AS 355F, basic rotorcraft flight manual, Revision 3, Code Date 87-10 and IFR rotorcraft flight manual supplement 11.4, Revision 3, Code Date 87-12. (3) For the Model AS 355F1, basic rotorcraft flight manual, Revision 2, Code Date 87-10, and IFR rotorcraft flight manual supplement 11.4, Revision 1, Code Date 87- 12. (c) To insure that the limited service life of the igniters defined in paragraph (a) above is properly identified and adhered to, the following updates (or future revisions thereto) must be incorporated in the Master Servicing Recommendations-Chapter 5-99 (Airworthiness Limitations): (1) AS 355E, Revision 15, Page 21. (2) AS 355F, Revision 15, Page 23. (3) AS 355F1, Revision 15, Page 23. (d) Upon accomplishing the requirements of paragraphs (a), (b), and (c) above, the placard required by paragraph (a) of AD 86-24-02 may be removed. (e) Upon request, an alternate means of compliance which provides an equivalent level of safety with the requirements of this AD may be used when approved by the Manager, Rotorcraft Standards Staff, ASW-110, FAA, Fort Worth, Texas 76193-0110. (f) Continuous ignition systems previously found to be equivalent methods of compliance with priority letter AD 86-24-02, dated November 21, 1986; or with Amdt. 39-5796 (52 FR 46985; December 11, 1987) effective January 27, 1988, are approved as equivalent methods of compliance to this AD. The procedure shall be done in accordance with SNIAS Service Bulletin AS 355 No. 80.02, Revision 2, approved July 8, 1987. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a)(1) and 1 CFR Part 51. Copies may be obtained from Aerospatiale Helicopter Corporation, 2701 Forum Drive, Grand Prairie, Texas 75053-4005. Copies may be inspected at the Office of the Regional Counsel, FAA, Southwest Region, 4400 Blue Mound Road, Fort Worth, Texas, or at the Office of the Federal Register, 1100 L Street, NW., Room 8401, Washington, D.C.This amendment supersedes AD 86-24-02, Amendment 39-5796, which was effective January 27, 1988. This amendment (39-6052, AD 89-01-01) becomes effective January 28, 1989.
89-24-03: 89-24-03 TELEDYNE CONTINENTAL MOTORS (TCM): Amendment 39-6386. Correction issued on May 8, 1990. Docket No. 89-ANE-19. Applicability: TCM Model TSIO-520-UB engines, serial numbers 515000 thru 515999 and 527000 thru 527070, and to all remanufactured and overhauled engines of this model, regardless of serial number, which are equipped with part number (P/N) 642668 turbocharger inlet assembly. Compliance: Required at the next 100 hour inspection or annual inspection, or within 100 flight hours, whichever occurs first after the effective date of this AD, and thereafter at intervals not to exceed 100 flight hours. To prevent possible cracking of the turbocharger inlet assembly which could result in engine compartment fire, accomplish the following: (a) Visually inspect turbocharger inlet assembly P/N 642668 for cracks especially in the weld joints just above the turbine inlet temperature boss. If a crack is found, replace P/N 642668 with P/N 646795 turbocharger inlet assembly, prior to further flight. (b) Make appropriate log book entry showing compliance with this AD. NOTES: (1) Beechcraft Aircraft Corporation Service Communique No. 70, dated October 28, 1983, refers to this subject. NOTES: (2) When determining the P/N assembly installed in order to comply with this AD, a distinguishing feature of the P/N 646795 turbocharger inlet assembly is 2 ribs (approximately 0.25 inches in height, 0.1 inches in width, and 2.1 inches in length) on the top of the turbocharger mating flange. NOTES: (3) If P/N 642668 is not installed, no action is required. (c) Aircraft may be ferried in accordance with the provisions of FAR 21.197 and 21.199 to a base where the AD can be accomplished. (d) Upon submission of substantiating data by an owner or operator through an FAA Airworthiness Inspector, an alternate method of compliance with the requirements of this AD or adjustments to the compliance schedule specified in this AD may be approved by the Manager,Atlanta Aircraft Certification Office, Federal Aviation Administration, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. This amendment 39-6386 (AD 89-24-03) became effective on December 4, 1989. This correction becomes effective on June 18, 1990.
98-20-38: This amendment adopts a new airworthiness directive (AD) that applies to Raytheon Aircraft Company (Raytheon) 200 series airplanes. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD was prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2022-09-11: The FAA is superseding Airworthiness Directive (AD) 2021-14- 17, which applied to certain Airbus SAS Model A350-941 and -1041 airplanes. AD 2021-14-17 required revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations. Since the FAA issued AD 2021-14- 17, the FAA has determined that new or more restrictive airworthiness limitations are necessary. This AD continues to require the revision of the existing maintenance/inspection program, and also requires revising the existing maintenance or inspection program, as applicable, to incorporate new or more restrictive airworthiness limitations, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
81-05-03: 81-05-03 THE BALLOON WORKS: Amendment 39-4053. Applies to Firefly Models 5, 6, 6B, 7, 7B and 8-24 series hot air balloons equipped with Fire 2 auxiliary heaters incorporating The Balloon Works fuel tanks part numbers BW 3229-A through BW 3229-N and BW 3307-A through BW 3307-H, certificated in all categories. Compliance required within the next 10 hours time in service after the effective date of this AD, unless already accomplished. To prevent inadvertent operation of the Fire 2 heater system during a hard landing, even though the tank valve has been closed, accomplish the following: Modify the Fire 2 fuel tank shut-off valve in accordance with The Balloon Works Service Bulletin B12 dated December 15, 1980, or later FAA approved revision, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southern Region. Make an appropriate maintenance record showing compliance with this AD. This amendment becomes effective March 11, 1981.
75-06-08: 75-06-08 GRUMMAN AMERICAN AVIATION CORPORATION: Amendment 39- 2124. Applies to G-1159 airplanes certificated in all categories. Compliance required within the next 150 hours' time in service after the effective date of this AD, unless already accomplished. To prevent possible loss of all DC and AC power, connect the battery switch ground leads to separate studs at the center overhead panel in accordance with Grumman ASC 188 or in an equivalent manner approved by Chief, Engineering and Manufacturing Branch, Southern Region, Atlanta, Georgia. This amendment becomes effective March 18, 1975.
2022-09-15: The FAA is adopting a new airworthiness directive (AD) for all Dassault Aviation Model FALCON 2000 and FALCON 2000EX airplanes. This AD was prompted by brake system failures during landing due to a brake servo-valve failure resulting from application of an inappropriate oil type during production and maintenance. This AD requires relocating affected servo-valves and revising the existing airplane flight manual (AFM) to provide temporary information necessary to operate airplanes fitted with at least one affected brake servo-valve, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. This AD also limits or prohibits the installation of affected brake servo-valves. The FAA is issuing this AD to address the unsafe condition on these products.
98-20-32: This amendment adopts a new airworthiness directive (AD), applicable to all Short Brothers Model SD3-60 SHERPA series airplanes, that requires an initial cleaning and visual inspection of the distance piece and adjacent side plates of the fuselage wing strut pick-up of the left- and right-stub wings to detect corrosion; rework or replacement of damaged components; and, for certain conditions, follow-on repetitive cleaning and visual inspections of reworked components. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to detect and correct corrosion of the distance piece and adjacent side plates, which could result in reduced strength of the wing strut attachment to the stub wing on the fuselage, and consequent reduced structural integrity of the main wing.
98-20-33: This amendment adopts a new airworthiness directive (AD) that applies to Cessna Aircraft Company (Cessna) Model T210R airplanes. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD was prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
2013-06-01: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) models Tay 620-15 and Tay 650-15 turbofan engines. This AD was prompted by RRD recalculating the Declared Safe Cyclic Life (DSCL) for certain low-pressure compressor (LPC) rotor disc assemblies operating to the Plan D Flight Mission. This AD requires removing the affected LPC rotor disc assemblies at a new lower recalculated DSCL. We are issuing this AD to prevent failure of the LPC rotor disc assembly, uncontained engine failure, and damage to the airplane.
2000-23-09: This amendment adopts a new airworthiness directive (AD), applicable to certain EMBRAER Model EMB-120 series airplanes, that requires a one-time inspection to detect wear of the hydraulic pump hoses, and corrective action, if necessary. This AD also requires relocation of the clip that secures the left forward hold-open rod of both nacelles. The actions specified by this AD are intended to prevent chafing and consequent rupture of the hydraulic line and loss of hydraulic pressure, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
98-20-28: This amendment adopts a new airworthiness directive (AD) that applies to Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 airplanes. This AD requires revising the FAA-approved Airplane Flight Manual (AFM) to specify procedures that would prohibit flight in severe icing conditions (as determined by certain visual cues), limit or prohibit the use of various flight control devices while in severe icing conditions, and provide the flight crew with recognition cues for, and procedures for exiting from, severe icing conditions. This AD is prompted by the results of a review of the requirements for certification of these airplanes in icing conditions, new information on the icing environment, and icing data provided currently to the flight crew. The actions specified by this AD are intended to minimize the potential hazards associated with operating these airplanes in severe icing conditions by providing more clearly defined procedures and limitations associated with such conditions.
77-13-01: 77-13-01 GRUMMAN AMERICAN AVIATION CORPORATION (GAAC): Amendment 39-2919 as amended by Amendment 39-3003 is further amended by Amendment 39-3183. Applies to GAAC Model G-159, all serial numbers, and Model G-1159, serial numbers 1 through 208 and 775, airplanes certificated in all categories. Compliance required within 10 hours time in service after June 21, 1977, unless already accomplished. To prevent injury to an occupant of any jumpseat located between fuselage stations 119 and 169 on GAAC Models G-159 and G-1159 airplanes, accomplish one of the following: (a) Install a placard either on the bulkhead adjacent to the jumpseat or at any equivalent location approved by the Federal Aviation Administration utilizing a minimum of 3/16 inch high letters with the wording: "JUMPSEAT OCCUPANCY DURING TAXI, TAKEOFF, OR LANDING PROHIBITED." or (b) Modify in the following manner: 1. The Model G-159 nose landing gear drag strut fused or bulkhead modification in accordance with GAAC Aircraft Service Change No. 226, Part I or II, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region. 2. The Model G-1159 nose landing gear wheel well bulkhead is modified to eliminate drag strut penetration in accordance with GAAC Aircraft Service Change No. 226, Part II, or later FAA approved revision, or in an equivalent manner approved by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, or (c) Upon a grant of extension of compliance time by the Chief, Engineering and Manufacturing Branch, FAA, Southern Region, the required placard may be removed for the length of the extension. Interested operators must furnish documentation with justification for the need for an extension to the Federal Aviation Administration, Chief, Engineering and Manufacturing Branch, P.O. Box 20636, Atlanta, Georgia 30320 by July 21, 1978. Also required in this documentation isevidence of a firm commitment from GAAC or a qualified modifier on the available date for the modification kit for that serial number aircraft. Each request for an extension will be handled on an individual aircraft basis. When either of the modifications described in paragraph b(1) or b(2) are accomplished, or the individual grant of extension is issued in accordance with paragraph (c), the required placard of paragraph (a) may be removed. However, grants of extension of compliance time will not be issued for any date beyond November 8, 1979. After November 8, any G-159 or G-1159 aircraft with a jumpseat installed between fuselage stations 119 and 169 must have installed either the modification in paragraph b(1) or b(2), or the placard in paragraph (a). Amendment 39-2919 became effective June 21, 1977. Amendment 39-3003 became effective August 8, 1977. This Amendment 39-3183 becomes effective April 21, 1978.
2013-06-02: We are adopting a new airworthiness directive (AD) for Diamond Aircraft Industries GmbH Models DA 42 M-NG and DA 42 NG airplanes. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as the engine air inlet filter is subject to icing. We are issuing this AD to require actions to address the unsafe condition on these products.
98-20-11: This amendment adopts a new airworthiness directive (AD), applicable to certain Saab Model SAAB SF340A and SAAB 340B series airplanes, that requires repetitive detailed visual inspections of the windshield wiper assembly for discrepant conditions, and corrective actions, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified by this AD are intended to prevent failure of the windshield wiper assembly, which could result in loss of visibility; or damage to the propeller(s), possible penetration of the fuselage skin, and consequent depressurization of the airplane.
72-20-01: 72-20-01 HAWKER SIDDELEY AVIATION LTD.: Amdt. 39-1523. Applies to Hawker Siddeley deHavilland Model DH-114 "Heron" airplanes. Compliance required as indicated. To prevent possible fatigue failure of the primary airplane structure accomplish the following: (A) Before the accumulation of the total hours' time in service specified in Column B for the applicable component specified in Column A, or within the next 100 hours' time in service after the effective date of this AD, whichever occurs later, and thereafter before the accumulation of the specified total hours' time in service on the replacement component, comply with the applicable paragraph of this AD specified in Column C: Column A Component Column B Service Life Column C AD Paragraph (1) Airframes 30,000 Hours (B) (2) Each component of an airframe not otherwise specified in this AD. 30,000 Hours (C) (3) Wing assemblies which do not incorporate modification 520, and fuselage center section lower spar booms, P/N 14FS2939 that do not incorporate modification 492. 3,500 Hours (D) (4) Wing assemblies that incorporate modification 520 and which have not been reworked in accordance with paragraph (e)(2). 15,000 Hours (E) (5) Wing assemblies which incorporate modification 520 that have been reworked in accordance with subparagraph (E)(2). 15,000 Hours' since reworked in accordance with subparagraph (E)(2) or 30,000 hours' total time in service whichever occurs first (E)(1) (6) Vertical fin front attachment fittings (R.H. and L.H.). 15,000 Hours (F) (7) Elevator trim tab connecting rods P/N 14TE.431A (R.H. and L.H. Elevator). 15,000 Hours (G) (B) Replace an airframe with an airframe of the same part number or a part number approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, that has accumulated less than 30,000 hours' time in service. (C) Replace each component of an airframe with a component of the same partnumber or a part number approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, that has accumulated less than 30,000 hours' time in service. (D) Comply with either of the following: (1) Replace the wing assembly with a wing assembly that has modification 520 incorporated and that has accumulated less than 15,000 hours' time in service, including the hours' time in service prior to the incorporation of Modification 520, and incorporate modification 492 on the wing carry-through structure in the fuselage center section in accordance with DeHavilland Aircraft Service Modification News Sheet, Modification No.: HERON 492, as amended through Amendment No. 3, dated March 6, 1956, or an FAA-approved equivalent. (2) Incorporate Modification 520 on the wing main spar lower boom in accordance with DeHavilland Aircraft Service Modification News Sheet, Modification No.: HERON 520, Issue 2, dated December 17, 1956, or an FAA-approved equivalent, and incorporate Modification 492 on the wing carry-through structure in the fuselage center section in accordance with DeHavilland Aircraft Service Modification News Sheet, Modification No.: HERON 492, as amended through Amendment No. 3, dated March 6, 1956, or an FAA-approved equivalent. (E) Comply with the following: (1) Replace the wing assembly with a Modification 520 Wing Assembly of the same part number that has accumulated less than 15,000 hours' time in service, including the hours' time in service prior to the incorporation of Modification 520, or (2) If the wing assembly has not accumulated 30,000 hours' time in service, including the hours' time in service prior to the incorporation of Modification 520, and the rework specified in this subparagraph has not been accomplished, rework the wing assembly as follows: (i) Rework the basic wing structure by incorporating modification 1585 in accordance with Hawker Siddeley Aviation Limited ModificationLeaflet "Civil Modification" for Modification No.: HERON 1585 with Amendment No. 4 incorporated, or an FAA-approved equivalent. (ii) Replace the existing flap datum hinge links with new links, P/N 14 WF.453 (L.H.) and P/N 14 WF.454(R.H.) or an FAA-approved equivalent, unless already accomplished within the last 4,000 hours' time in service; (iii) Replace the existing forward fork joint fittings (P/N 14 WF.1) and the forward eye joint fittings (P/N 14 WF.3), located between the inner and center flap sections with new fittings of the same part numbers in accordance with Hawker Siddeley Aviation Limited Repair Drawing RD. 14 WF.109, dated January 23, 1970, or an FAA-approved equivalent; (iv) Replace the small angle brackets located on the forward face of the rear vertical flange at wing rib No. 01 near the inner flap section inner hinge bracket attachment with new brackets, P/N 14 W.5621 and 14 W.5623 (Modification 1076, full version) or an FAA-approved equivalent.(v) Replace the engine mounting pickup straps, P/N 14-2W.555ND, and strap doublers, P/N 14 W.1715ND, with new straps and strap doublers of the same part numbers in accordance with paragraph 5.2 of Hawker Siddeley Aviation Limited, Technical News Sheet; Series: HERON (114) No. W.15, Issue 1, dated October 27, 1969, or an FAA- approved equivalent; and (vi) Replace the magnesium parts in the flap hinge assemblies with aluminum-copper alloy parts by incorporating modification 1098 in accordance with Hawker Siddeley Aviation Modification Leaflet "Civil Modification" for Modification No. HERON 1098, with Amendment No. 2 incorporated, or an FAA-approved equivalent. (F) Replace - (1) Vertical fin front attachment fittings with new fittings, P/N's 14.FS-4669 (left hand) and 14.FS-4670 (right hand), in accordance with DeHavilland Aircraft Service, Modification News Sheet No. HERON 869, dated December 12, 1956, or an FAA-approved equivalent, and (2) Vertical Channels,P/N's 14FS.187 (left hand) and 14FS.188 (right hand) on the aft face of the stub fin portion of Bulkhead 6 with new channels of the same part number in accordance with Hawker Siddeley Aviation Limited, Repair Drawing RD.14FS.293, dated February 10, 1972, or an FAA-approved equivalent. (G) Replace elevator trim tab connecting rods, P/N 14 TE.431A, and fork engs, P/N 4T.55 (two each per airplane), with new rods and fork ends of the same part number. (H) Operators who have not kept records of hours' time in service on any part to which a provision of the AD applies shall substitute airplane hours' time in service in lieu thereof. (Hawker Siddeley Aviation Limited, Technical News Sheet; Series: HERON (114) No. M.9, Issue 2, dated July 3, 1972, covers this same subject.) This amendment is effective upon publication in the Federal Register as to all persons except those persons to whom it was made immediately effective by the airmail letter dated July 27, 1972 which contained this amendment.