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91-16-02: 91-16-02 AIRBUS INDUSTRIE: Amendment 39-7092. Docket No. 91-NM-59-AD. Applicability: Model A320 series airplanes, on which Modification 22039 has not been accomplished, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To ensure complete closure of the low pressure fuel fire shut-off valve, accomplish the following: A. Within 350 hours time-in-service after the effective date of this AD, and thereafter at intervals not to exceed 350 hours time-in-service, perform a functional check of the low pressure fuel fire shut-off valve actuator, in accordance with Airbus Industrie All Operators Telex (AOT) 28-01, dated October 8, 1990. B. If any valve fails or indicates failure to open or close correctly, prior to further flight, replace the low pressure fuel fire shut-off valve actuator with either P/N HTE 190001 (PRE Airbus Industrie Service Bulletin A320-28-1028), or P/N HTE 190001-1 (POST Airbus Industrie ServiceBulletin A320-28-1028), in accordance with Airbus Industrie Service Bulletin A320-28-1028, Revision 1, dated November 23, 1990. Following actuator replacement, perform a functional test in accordance with AOT 28-01, dated October 8, 1990. Accomplishment of Modification 22039 (Service Bulletin A320-28-1028) constitutes terminating action for the repetitive functional checks required by paragraph A. of this AD. C. An 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113. D. Special 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. E. The repetitive functional check requirements shall be done in accordance with Airbus Industrie All Operators Telex (AOT) 28-01, dated October 8, 1990. The replacement requirements shall be done in accordance with Airbus Industrie Service Bulletin A320-28-1028, Revision 1, dated November 23, 1990. 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 Airbus Industrie, Airbus Support Division, Avenue Didier Daurat, 31700 Blagnac, France. Copies may be inspected at the FAA, Transport Airplane Directorate, Renton, Washington; or at the Office of the Federal Register, 1100 L Street N.W., Room 8401, Washington, D.C. This amendment (39-7092, AD 91-16-02) becomes effective on September 11, 1991.
2022-26-05: The FAA is adopting a new airworthiness directive (AD) for all Rolls-Royce Deutschland Ltd & Co KG (RRD) TAY 620-15 and TAY 650-15 model turbofan engines. This AD was prompted by reports of cracks on the high-pressure turbine (HPT) stage 2 intermediate air seal attachment bolts (attachment bolts). This AD requires repetitive inspections of the HPT stage 2 intermediate air seal and attachment bolts and, depending on the results of the inspections, replacement of attachment bolts and the HPT stage 1 and stage 2 rotor disks, 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.
2001-16-07: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-400 and 767 series airplanes, that requires modification of the core cowl assemblies of the engines. This action is necessary to prevent failure of the core cowl latches during an engine fire, and consequent in-flight separation of an engine core cowl and its strut fire barrier from the airplane. This action is intended to address the identified unsafe condition.
87-02-06: 87-02-06 GATES LEARJET: Amendment 39-5520. Applies to the following Gates Learjet series airplanes, models/serial numbers listed below, certificated in any category; except those airplanes equipped with Part Number (P/N) 2651034 forward engine mount assembly due to spare replacements: MODEL SERIAL NUMBER 35 001 through 522 36 001 through 053 55 001 through 107 Compliance required as indicated, unless previously accomplished. To ensure the structural integrity of the forward engine mounts, accomplish the following: A. Prior to the accumulation of 2,400 hours time-in-service or 2,400 landings (whichever occurs first), or within the next 75 hours time-in-service after the effective date of this AD, whichever occurs later, conduct a visual inspection of the installed left and right forward engine mounts in accordance with Paragraph 2A of Gates Learjet Service Bulletin 35/36-71-3 or 55-71-2, both dated January 5, 1987, or later FAA-approved revision, as appropriate. 1. If no cracks are found, repeat the visual inspection at intervals not to exceed 420 hours time-in-service. 2. If cracks are found, inspect or replace as indicated below: a. For total visible crack length (forward plus aft) of 1.0 inch or more, prior to further flight accomplish one of the following: (1) Replace cracked mount(s) with P/N 2651034 mount assembly; or (2) Conduct the magnetic particle inspection and disposition in accordance with paragraph B. of this AD. b. For total visible crack length (forward plus aft) of less than 1.0 inch, accomplish one of the following: (1) Replace the cracked mount(s) with P/N 2651034 mount assembly within the next 420 hours time-in-service; or (2) Conduct the magnetic particle inspection and the next 420 hours time-in-service. B. Prior to the accumulation of 2,400 hours time-in-service or 2,400 landings (whichever occurs first), or within the next 1,500 hours time-in-service after the effective date of this AD, whichever occurs later, conduct a magnetic particle inspection of the removed left and right engine mounts, in accordance with Paragraph 2B of Gates Learjet Service Bulletin 35/36- 71-3 or 55-71-2, both dated January 5, 1987, or later FAA-approved revisions, as appropriate. 1. If no cracks are found, repeat the inspection at intervals not to exceed 1,500 hours time-in-service. 2. If cracks are found, replace as indicated below: a. For total crack lengths (forward plus aft) of 3.0 inches or more, replace cracked mount(s) with P/N 2651034 mount assembly prior to further flight. b. For total crack lengths (forward plus aft) of less than 3.0 inches, replace cracked mount(s) with P/N 2651034 mount assembly within 420 hours time-in-service. C. The installation of a P/N 2651034 mount assembly constitutes terminating action for the repetitive inspections required by paragraphs A. and B. of this AD. D. Duplicate copiesof the Compliance Response form, included in Gates Learjet Service Bulletins 35/36-71-3 and 55-71-2, both dated January 5, 1987, used for reporting the results of the initial visual and magnetic particle inspections, must be submitted within one week after the inspection to the FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209. E. Special 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. F. Alternate means of compliance, which provide an acceptable level of safety, may be used when approved by the Manager, Wichita Aircraft Certification Office, FAA, Central Region. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Gates Learjet Corporation, P.O. Box 7707, Wichita, Kansas 67277. This information may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid- Continent Airport, Wichita, Kansas. This amendment becomes effective February 6, 1987.
90-25-06: 90-25-06 CESSNA AIRCRAFT COMPANY: Amendment 39-6818. Docket No. 90-NM-253-AD. Applicability: Model 650 Series airplanes; Serial Nos. 650-0094 through -0096, -0098, -0136 through -0139, -0149, -0161, -0167, -0170, -0172, -0173, -0176 through 0182, -0184 through -0189, and -0192; equipped with Honeywell SPZ-8000 Digital Automatic Flight Control System; certificated in any category. Compliance: Required within 25 hours time-in-service after the effective date of this AD, unless previously accomplished. To prevent complete loss of the pilots' primary flight instrument displays, accomplish the following: A. Replace the distance measuring equipment (DME) antenna cable connectors in accordance with Steps l through 3 of the Accomplishment Instructions of Cessna Citation Alert Service Bulletin A650-34-68, dated November 2, 1990. B. Accomplish either subparagraph B.1. or B.2., below: 1. Check the electrical bonding of the DME antennas to airplane structurein accordance with Step 4 of the Accomplishment Instructions of Cessna Citation Alert Service Bulletin A650-34-68, dated November 2, 1990. a. If the resistance is greater than 0.010 Ohms, prior to further flight, rework the antennas installation in accordance with Step 4 of the service bulletin. b. If the resistance is equal to or less than 0.010 Ohms, restore the system for use in accordance with Steps 5 through 7 of the Accomplishment Instructions of the service bulletin. 2. Rework the antenna installation in accordance with Step 4 of Cessna Citation Alert Service Bulletin A650-34-68, dated November 2, 1990; and restore the system for use in accordance with Steps 5 through 7 of the Accomplishment Instructions of the service bulletin. C. 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, Wichita Aircraft Certification Office (ACO), ACE-130W, FAA, CentralRegion. NOTE: The request should be submitted directly to the Manager, Wichita ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Manager, Wichita ACO. D. Special 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. All persons affected by this directive who have not already received the appropriate service information from the manufacturer may obtain copies upon request to Cessna Aircraft Company, Customer Services, P.O. Box 1521, Wichita, Kansas 67201. This information may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 1601 Lind Avenue S.W., Renton, Washington; or at the FAA, Central Region, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Wichita, Kansas. This amendment (39-6818, AD 90-25-06) becomes effective on December 11, 1990.
2016-25-22: We are adopting a new airworthiness directive (AD) for all Viking Air Limited Models DHC-2 Mk. I, DHC-2 Mk. II, and DHC-2 Mk. III airplanes that supersedes AD 2016-19-08. 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 corrosion of the elevator control rod and of the elevator actuating lever on the control column, which could cause these components to fail. We are issuing this AD to require actions to address the unsafe condition on these products.
74-15-06: 74-15-06 SIKORSKY AIRCRAFT: Amendment 39-1890 as amended by Amendment 39-2134 and 39-2447 is further amended by Amendment 39-3089. Applies to all S-58 model series helicopters equipped with magnesium input and/or intermediate housings. Compliance required as indicated unless already accomplished. To preclude possible failure of the magnesium input and/or intermediate housings of the tail rotor gearbox assembly, P/N S1635-64000 series, accomplish the following: 1. Within the next three hours time in service after the effective date of this AD, or whenever unusual vibration in the tail rotor system is experienced, accomplish the following in accordance with the instructions set forth in Section 2, Paragraphs A and C of Sikorsky Service Bulletin No. 58B35-17C, dated November 24, 1975 (hereinafter Bulletin No. 58B35-17C). a. Inspect the nuts attaching the tail rotor gearbox assembly to the pylon fitting. b. Inspect the input and intermediate housings of the gearbox. c. Retorque the nuts that attach the input to intermediate housing. 2. After completion of the initial inspections required in Paragraph 1, conduct the repetitive inspections specified in a, b, and c below as applicable. Sections and paragraphs listed are part of Bulletin No. 58B35-17C. a. Every ten hours time in service inspect in accordance with Section 2, Parargraphs A(2) and C(2), (a) thru (d), if both Sikorsky Service Bulletins listed below are not complied with or lightweight input and/or intermediate tail rotor gearbox housings are installed: (1) 58B15-14B, Balance of Rotary Rudder Assembly. (2) 58B20-14B, Strengthening of Pylon Carry-Thru Structure of Rotary Rudder Assembly. b. Every 20 hours time in service, inspect in accordance with Section 2, Paragraphs C(2), (a) thru (d), if tail rotor gearbox S1635-64000-9 is installed and if both Sikorsky Service Bulletins 58B15-14B and 58B20-14B or their latest FAA approved revisions are compliedwith. c. Every 50 hours time in service, inspect in accordance with Section 2, Paragraphs C(2), (a) thru (d), if tail rotor gearbox S1635-64000-10 is installed and if both Sikorsky Service Bulletins 58B15-14B and 58B20-14B or their latest FAA approved revisions are complied with. 3. Within the next 25 hours time in service after the effective date of this AD, remove the tail rotor gearbox assembly (P/N S1635-64000 series) from the aircraft and accomplish the one-time inspection set forth in Section 2, Paragraph B, of Bulletin No. 58B35-17C. 4. Every 50 hours time in service after the inspection required in Paragraph 1 above, inspect the nuts attaching the tail gearbox to the pylon fitting in accordance with Section 2, Paragraph A(1) of Bulletin No. 58B35-17C. If heavy weight input housing, P/N S1635-64009-3N, and heavyweight intermediate housing, P/N S1635-64074, are both installed, inspect in accordance with Section 2, Paragraph D(2), of Bulletin No. 58B35-17C. 5. Tail rotor gearbox assembly (P/N S1635-64000 series) input and intermediate housings and pylon fittings (S1620-64129) found to have evidence of cracks shall be replaced with an acceptable assembly prior to further flight. All other defects found as a result of the inspections required by Paragraphs 1, 2, 3, and 4 shall be repaired in accordance with instructions contained in Bulletin No. 58B35-17C prior to further flight. 6. Remove from service magnesium input and intermediate housings P/N's S1635-64009-3N, S1635-64074, S1635-64009, S1635-64010 as follows: a. Prior to July 31, 1978, for all turbine engine powered S-58T helicopters. b. Prior to December 31, 1978, for all piston engine powered S-58 helicopters. Replace with aluminum input and intermediate housings S1635-64009-101 and S1635-64074-103 respectively. NOTE: Sikorsky Service Bulletin No. 58B35-25 covers this subject. 7. Upon submittal of substantiating data through a Federal Aviation Administration inspector, the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, New England Region, may adjust the compliance time. The manufacturer's specifications and procedures identified and described in this directive are incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). All persons affected by this directive who have not already received these documents from the manufacturer may obtain copies upon request to Sikorsky Aircraft, Division of United Aircraft Corporation, Stratford, Connecticut 06602. These documents may also be examined at the Office of the Regional Counsel, New England Region, Federal Aviation Administration, 12 New England Executive Park, Burlington, Massachusetts 01803 and at Federal Aviation Administration Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the Federal Aviation Administration at its headquarters in Washington, D.C., and at the New England Regional Office in Burlington, Massachusetts. Amendment 39-1890 became effective July 27, 1974. Amendment 39-2134 became effective April 3, 1975. Amendment 39-2447 became effective December 10, 1975. This amendment 39-3089 becomes effective December 30, 1977.
73-26-01: 73-26-01 PIPER: Amdt. 39-1754 as amended by Amendment 39-1772. Applies to Model PA-25 airplanes Serial Numbers 25-1 through 25-1999, PA-25-235 and PA-25-260, Serial Numbers 25-02 and 25-2000 through 25-74005573, certificated in all categories. Compliance required as indicated. For Model PA-25-235 and Model PA-25-260 airplanes with forward wing spar(s) with 2000 hours or more time in service on the effective date of this AD, compliance is required within 5 hours time in service after the effective date of this AD, unless already accomplished within the last 295 hours time in service, and thereafter at intervals not to exceed 300 hours time in service from last inspection. For Model PA-25-235 and Model PA-25-260 airplanes with forward wing spar(s) with less than 2000 hours time in service on the effective date of this AD, compliance is required upon accumulation of 2000 hours time in service or within the next 5 hours time in service, whichever is later, unless already accomplished within the last 295 hours time in service, and thereafter at intervals not to exceed 300 hours time in service from last inspection. For Model PA-25 (150 h.p.) airplanes, compliance is required upon accumulation of 2000 hours wing spar time in service or within the next five hours time in service after the effective date of this AD, whichever is later, unless already accomplished. To detect cracks in the forward wing spar, accomplish the following: (a) Remove left and right wing from fuselage. (b) Remove wing attach fitting located on each forward wing spar root. (c) Using standard dye or fluorescent penetrant inspection procedures, or equivalent approved by the Chief, Engineering and manufacturing Branch, FAA Southern Region, inspect the following areas for cracks: 1. The inboard end of left and right forward spar web and doubler in the area of wing spar attach fitting bolt holes. 2. The left and right forward spar lower cap rear flange aroundthe inboard four skin attachment holes. (d) If cracks are found as a result of the inspections required in paragraph (c), the affected parts must be replaced with serviceable parts of the same part number or repaired in accordance with the instructions contained in Piper Service Bulletin No. 414, before further flight. (e) When Piper Kit No. 760840, Spar Web Reinforcement Plate or equivalent approved by the Chief, Engineering and Manufacturing Branch, FAA Southern Region, is installed immediately after inspection and repair as required by this AD, repetitive inspections at 300 hour intervals are no longer necessary. (f) Report in writing within 10 days any cracks found during the inspections required by this AD to Chief, Engineering and Manufacturing Branch, ASO-210, FAA, Southern Region, P.O. Box 20636, Atlanta, Georgia 30320. Each report must include aircraft model, serial and registration numbers, location of cracks, length of cracks and number of hours wing spar time in service. (Reporting approved by the Bureau of the Budget under BOB No. 04-R0174.) Piper Service Bulletin No. 410 pertains to the inspections required by this AD and Piper Service Bulletin No. 414 pertains to Piper Kit No. 760840, Spar Web Reinforcement Plate. Amendment 39-1754 became effective December 17, 1973 for all persons except those to whom it was made effective upon receipt of the airmail letter dated December 7, 1973 which contained this amendment. The Amendment 39-1772 becomes effective January 28, 1974.
2001-16-19: This amendment adopts a new airworthiness directive (AD), applicable to all Boeing Model 747-100 and -200 series airplanes modified by supplemental type certificate ST00196SE, that requires modification of the in-flight entertainment (IFE) system and revision of the Airplane Flight Manual. This action is necessary to ensure that the flight crew is able to remove electrical power from the IFE system when necessary and is advised of appropriate procedures for such action. Inability to remove power from the IFE system during a non-normal or emergency situation could result in inability to control smoke or fumes in the airplane flight deck or cabin. This action is intended to address the identified unsafe condition.
91-14-05: 91-14-05 AVCO LYCOMING: Amendment 39-6955. Docket No. 91-ANE-09. Applicability: Avco Lycoming ALF 502L series turbofan engines installed on, but not limited to the Canadair Challenger CL601 aircraft. Compliance: Required as indicated, unless previously accomplished. To prevent complete loss of engine power, uncontained disk failure, and possible damage to the aircraft, accomplish the following: (a) Clean, visually inspect, coat with "Sermetel W" or "ALSEAL-518" and reidentify third stage high compressor (HC) rotor disks in accordance with Textron Lycoming Service Bulletin (SB) ALF 502L 72-203, Revision 3, dated December 7, 1990, as follows: (1) For those third stage HC disks with 7,000 cycles since new (CSN) or greater on the effective date of this AD, within the next 500 cycles in service, not to exceed 8,500 CSN. (2) For those third stage HC disks with less than 7,000 CSN on the effective date of this AD, at or prior to accumulating a total of 7,500 CSN. (b) Remove, prior to further flight, third stage HC disks found with evidence of corrosion pitting or cracks. (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 times specified in this AD may be approved by the Manager, Engine Certification Office, Engine and Propeller Directorate, Aircraft Certification Service, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803-5299. The inspection procedures shall be done in accordance with the following Textron Lycoming service bulletin: Document No. Page No. Issue/Revision Date ALF 502L 72-203 1, 2, 4 3 December 7, 1990 ALF 502L 72-203 3, 6 2 August 8, 1990 ALF 502L 72-203 5 1 June 16, 1989This 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 Textron Lycoming, 550 Main Street, Stratford, Connecticut 06497. Copies may be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street NW, Room 8401, Washington, D.C. This amendment (39-6955, AD 91-14-05) becomes effective on July 15, 1991.