Results
89-23-09: 89-23-09 EMPRESA BRASILEIRA DE AERONAUTICA, S.A. (EMBRAER): Amendment 39-6372. Docket No. 89-NM-89-AD. Applicability: Model EMB-120 series airplanes; Serial numbers 120004, 120006 through 120070, 120072 through 120080, and 120082 through 120099; certificated in any category. Compliance: Required within 180 days after the effective date of this AD, unless previously accomplished. To prevent a gear-up landing due to malfunction of the landing gear aural warning system, accomplish the following: A. Modify the landing gear aural warning system and calibrate new switches, in accordance with either EMBRAER Service Bulletin No. 120-032-0055 dated March 16, 1989, or EMBRAER Service Bulletin No. 120-032-0052, dated March 15, 1989. 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, Atlanta Aircraft Certification Office, FAA, Central Region. NOTE: The request for an alternate means of compliance or an adjustment of the compliance time should be forwarded through an FAA Maintenance Inspector, who will either concur or comment and then send it to the Atlanta Aircraft Certification Office. C. 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 documents from the manufacturer may obtain copies upon request to EMBRAER, 276 S.W. 34th Street, Fort Lauderdale, Florida 33315. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or the FAA, Central Region, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia. This amendment (39-6372, AD 89-23-09) becomes effective on December 1, 1989.
68-10-04: 68-10-04 GENERAL DYNAMICS: Amendment 39-597 as amended by Amendment 39- 1305 is further amended by Amendment 39-2247. Applies to Models 340, 440, and C-131E airplanes including those using turbo propeller power. Compliance required as indicated. Due to several reports of cracks in the front spar lower rail which can result in failure of the outboard wing, accomplish the following: (a) For airplanes with 23,500 or more hours time in service on the effective date of this AD, inspect each front spar lower rail per (c) within the next 300 hours time in service, unless already accomplished within the last 700 hours time in service, and thereafter at intervals not to exceed 1000 hours time in service from the last inspection, and, if cracks are found, repair per (d) before further flight (except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be accomplished). (b) For airplanes with less than 23,500 hours time in service on the effective date of this AD, inspect each front spar lower rail per (c) before the accumulation of 23,800 hours time in service, and thereafter at intervals not to exceed 1000 hours time in service from the last inspection, and, if cracks are found, repair per (d) before further flight (except that the airplane may be flown in accordance with FAR 21.197 to a base where the repair can be accomplished). (c) Remove the wig leading edge and visually inspect the wing front spar lower rail between wing stations 240 and 490 for cracks. NOTE: During the inspection required by (c), pay particular attention to the areas immediately adjacent to the leading edge joints at wing stations 248, 264, 363 and 484. All reported cracks have originated in the rail forward flange at or near the leading edge attach screw holes. (d) If a crack is confined to the wing front spar lower rail, repair in accordance with General Dynamics/Convair Service Engineering Report No. 057-0/67-340-64/440-64/640-35, (Revision 1 or later FAA approved Revision) or a method approved by the Chief, Aircraft Engineering Division, Federal Aviation Administration, Western Region. If a crack extends beyond the spar rail into adjacent components, repair in accordance with a method approved by the Chief, Aircraft Engineering Division, FAA Western Region. (e) The repetitive inspections required in (a) and (b) may be discontinued when all cracks, if any, have been repaired per (d) and, unless already accomplished per (d), a reinforcing strap has been installed per details (a) and (b), Figure 1, of General Dynamics/ Convair Service Engineering Report No. 057-0/67-340-64/440-64/640-35 or a rework approved by the Chief, Aircraft Engineering Division, FAA Western Region has been accomplished. (f) Upon request of the operator, an FAA Air Carrier Maintenance Inspector, subject to prior approval of the Regional Director, FAA Western Region, may adjust the repetitive inspection intervals specified in this AD to permit compliance at an established inspection period of the operator if the request contains substantiating data to justify the increase for that operator. Amendment 39-597 became effective on May 14, 1968. Amendment 39-1305 became effective October 8, 1971. This amendment 39-2247 becomes effective July 30, 1975.
90-15-13: 90-15-13 MITSUBISHI HEAVY INDUSTRIES, LTD (formerly Nihon Aeroplane Manufacturing Company, NAMC): Amendment 39-6657. Docket No. 90-NM-29-AD. Applicability: Model YS-11 and YS-11A series airplanes, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent incidents of propellers failing to withdraw, accomplish the following: A. Within 1,000 flight hours after the effective date of this AD: 1. Inspect the propeller high stop withdrawal relay in accordance with the accomplishment instructions of Mitsubishi NAMC YS-11 Service Bulletin 61-5, dated December 20, 1988. If any abnormality is detected, replace the relay prior to further flight. 2. Install Decal 01-81717-27 in accordance with Mitsubishi NAMC YS-11 Service Bulletin 15-27, dated December 20. 1988. B. Repeat the inspection of the propeller high stop withdrawal relay at intervals not to exceed 3,000 flight hours after the initial inspection orafter replacement, in accordance with Mitsubishi NAMC YS-11 Service Bulletin 61-5, dated December 20, 1988. If any abnormality is detected, replace the relay prior to further flight. C. 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. D. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used if approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. NOTE: The request should be submitted directly to the Manager, Los Angeles ACO, and a copy sent to the cognizant FAA Principal Inspector (PI). The PI will then forward comments or concurrence to the Los Angeles ACO. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to NagoyaAircraft Works Mitsubishi Heavy Industries, Ltd., 10 Oye-cho, Minato-Ku, Nagoya 455, Japan; Attention: K. Saitoh, Manager, YS- 11 Group, Service Department. These documents may be examined at the FAA, Northwest Mountain Region, Transport Airplane Directorate, 17900 Pacific Highway South, Seattle, Washington, or at the Los Angeles Aircraft Certification Office, 3229 East Spring Street, Long Beach, California. This amendment (39-6657, AD 90-15-13) becomes effective on August 20, 1990.
69-24-03: 69-24-03 MARVEL-SCHEBLER: Amdt. 39-881. Applies to Marvel Schebler Models MA-3-A, MA-3-PA, MA-3-SPA, MA-4-SPA, MA-4-5, MA-5, MA-4-5-AA, MA-6AA, and HA-6 carburetors of the following listed part numbers and serial numbers installed on the Continental, Franklin and Lycoming model engines as specified below, to wit: ENGINE MANUFACTURER & MODEL CARBURETOR MODEL CARBURETOR PART NUMBER CARBURETOR SERIAL NUMBERS CONTINENTAL A-65 & A-75 Series MA-3-PA A-10-4233 P-22-460 thru P-22-464 O-200 Series MA-3-SPA A10-4115-1 AV-4-4094 O-200 Series MA-3-SPA A10-4894 BE-14-10218 thru BE-15-11672 C-85 Series MA-3-SPA A10-4240 AU-15-235 thru AU-15-244 C-90 Series MA-3-SPA A10-4252 Q-23-2422 thru Q-23-2436 C-145 Series MA-3-SPA A10-4895 BF-14-3598 thru BF-15-3655 O-470-K MA-4-5 A10-3965-12 H-3-6894 thru H-3-6896 O-470-R MA-4-5 A10-4893 BD-13-3946 thru BD-15-4660 FRANKLIN 4A-235 Series MA-3-SPA A10-4654 BN-3-112 thru BN-3-130 GA-335 Series MA-5 A10-4865 BC-14-530 thru BC-16-706 6V-350 Series MA-5 A10-4809 BA-14-203 thru BA-14-207 6A-350 Series MA-5 A10-4865 BC-14-530 thru BC-16-706 LYCOMING O-235 Series MA-3-A A10-3103-1 Y-30-3132 thru Y-30-3275 O-235 Series MA-3-A A10-4953 BV-0-268 thru BV-0-538 O-235 Series MA-3-PA A10-4978-1 BQ-3-252 thru BQ-3-276 O-235 Series MA-3-PA A10-5050 BY-0-100 thru BY-1-291 O-290 Series MA-3-SPA A10-3346-1 B-35-342 thru B-36-359 O-320 Series MA-4-SPA A10-3678-32 A-25-14781 thru A-26-16246 O-320 Series MA-4-SPA A10-5009 BL-5-2632 thru BL-5-3435 O-360 Series MA-4-5 A10-3878 G-34-4651 thru G-36-5362 O-360 Series MA-4-5 A10-4164-1 K-27-6460 thru K-27-6602 O-360 Series MA-4-5 A10-5034 BU-0-283 thru BU-0-383 O-360 Series HA-6 A10-5045 BW-0-198 thru BW-4-550 VO-435 Series MA-4-5-AA A10-4025-12 Z-16-2304 thru Z-18-2434 TVO-435 Series MA-6-AA A10-4438-1 AH-19-3676 thru AH-21-4067 O-540 Series MA-4-5 A10-4404 R-24-6530 thru R-26-6916 O-540 Series MA-4-5 A10-4404-1 AO-20-3571 thru AO-23-3829 O-540 Series MA-4-5 A10-5042 BS-1-427 thru BS-1-588 O-540 Series MA-4-5 A10-5054 BZ-0-100 thru BZ-0-209 VO-540 Series MA-6-AA A10-4218-1 AK-17-1274 thru AK-19-1478 VO-540 Series MA-6-AA A10-4975 BK-2-125 thru BK-3-148 NOTE: The affected carburetors listed above were manufactured between December 5, 1968, and June 23, 1969. Approximately 25% of these carburetors have been inspected and cleaned by Marvel Schebler or the manufacturers of the engines or aircraft on which the carburetors are installed. Marvel Schebler Service Bulletin A1-69 lists the carburetors remaining to be inspected and covers the same subject matter as this AD. Any carburetor serial numbers included in this AD but not listed on Marvel Schebler Service Bulletin A1-69 comply with this AD, and require no further inspection or cleaning. A logbook entry of compliance and nameplate marking must be made on these unlisted carburetors. The "A" prefix to the part numbers listed above does not appear on the carburetor nameplate. Compliance: Required within the next 25 hours' time in service after the effective date of this AD, unless previously accomplished. To prevent possible power losses due to blockage of carburetor metering passeges by thread lubricant or other foreign material, accomplish the following or an equivalent procedure approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region, or Chief, Engineering and Manufacturing Branch, FAA, Eastern Region: Remove the carburetor bowl drain plug with the aircraft fuel valve in the "ON" position and allow the carburetor to flush for 20 to 30 seconds. The auxiliary pump, if installed, should be operating. After flushing, inspect the drain plug cavity and drain plug for thread lubricant or other foreign material and remove any such material noted. After cleaning, reflush 20 to 30 seconds, reinstall plug approximately one thread into cavity, apply Parker Seal Lube or equivalent on exposed threads and tighten. NOTE: If practical, aircraft should be positioned so that bottom of bowl slopes toward drain opening during flushing and cleaning. Recommended torque for 1/8" pipe plug is 50-60 in. lbs., for 1/4" pipe plug is 120-144 in. lbs. After completion of the above, impression stamp or engrave "A1" on a nameplate or apply approximately 1/4-inch diameter dot of yellow enamel or similar permanent material to nameplate. This amendment becomes effective November 29, 1969.
2009-21-07: The FAA is adopting a new airworthiness directive (AD) for General Electric Company (GE) CF6-80C2 series turbofan engines with certain thrust reverser ballscrew gearbox assembly adjustable-length end actuators installed. This AD requires initial visual inspections and repetitive replacements of the 3/8-inch rod-ends installed on the thrust reverser ballscrew gearbox assembly adjustable-length end actuators. This AD also allows an optional terminating action to those repetitive replacements. This AD also requires initial visual inspections and replacements, if necessary, of the other hardware connecting the thrust reverser transcowls to the engine. This AD results from reports of four failures of rod-ends on certain thrust reverser ballscrew gearbox assembly adjustable-length end actuators, leading to partial or complete separation of the transcowl from the engine and airplane during thrust reversal. We are issuing this AD to prevent asymmetric thrust and loss of thrust control.
97-15-04: This amendment supersedes an existing airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 214B, 214B-1, and 214ST helicopters, that currently establishes a mandatory retirement life of 60,000 high-power events for the main transmission upper planetary carrier (carrier). This amendment requires changing the method of calculating retirement life for the carrier from high-power events to a maximum accumulated Retirement Index Number (RIN) of 120,000. This amendment is prompted by fatigue analyses and tests that show certain carriers fail sooner than originally anticipated because of the unanticipated high number of lifts or takeoffs (torque events) performed with those carriers in addition to the time-in-service (TIS) accrued under other operating conditions. The actions specified by this AD are intended to prevent fatigue failure of the carrier, which could result in failure of the main transmission and subsequent loss of control of the helicopter.
91-12-06: 91-12-06 GROB LUFT UND RAUMFAHRT: Amendment 39-7017. Docket No. 91- CE-05-AD. Applicability: Model G 109B motor gliders (serial numbers 6200 through 6362), certificated in any category. Compliance: Required within the next 3 calendar months after the effective date of this AD, unless already accomplished. To prevent separation of the studs in the root rib stud plate that could result in loss of the aileron and airbrake control systems, accomplish the following: (a) Inspect the security of the studs in the root rib stud plate (part number 109B- 4108) in accordance with the instructions in GROB Service Bulletin No. TM-817-29, dated August 6, 1990. If any loose studs are found, prior to further flight, repair the stud plate in accordance with the instructions in the referenced SB. (b) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate the motor glider to a location where the requirements of this AD can be accomplished.(c) An alternative method of compliance or adjustment of the compliance time that provides an equivalent level of safety may be approved by the Manager, Brussels Aircraft Certification Office, Europe, Africa, and Middle East Office, FAA, c/o American Embassy, B- 1000 Brussels, Belgium; Telephone (322) 513.38.30. The request should be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Brussels Aircraft Certification Office. (d) All persons affected by this directive may obtain copies of the document discussed in this AD upon request to GROB Luft und Raumfahrt, D-8939 Mattsies, Federal Republic of Germany; or may examine this document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106. This amendment (39-7017, AD 91-12-06) becomes effective on July 5, 1991.
2009-24-05: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) issued by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: Under certain ambient conditions, ice can accumulate on the walls of the fuel pipes within the aircraft fuel system, which can then be released downstream when fuel flow demand is increased. This released ice can then collect on the fuel-to-oil heat exchanger (FOHE) front face and limit fuel flow through the FOHE. We are issuing this AD to prevent ice from blocking the FOHE, which could result in an unacceptable engine power loss, and loss of control of the airplane.
77-14-05: 77-14-05 BRITISH AIRCRAFT CORPORATION: Amendment 39-2953. Applies to BAC 1- 11 200 and 400 series airplanes, certificated in all categories, with Garrett AiResearch Models GTCP 85-115, -115C or -115CK APU's installed, that do not have British Aircraft Corporation Modification PM 5217 incorporated. Compliance is required as indicated. To prevent excessive fuel contamination of the Auxiliary Power Unit oil contents, accomplish the following: (a) Within the next 60 APU hours' time in service after the effective date of this AD, unless accomplished within the last 20 APU hours' time in service, and thereafter at intervals not to exceed 80 APU hours' time in service from the last inspection, inspect for fuel leakage in accordance with paragraph 2.1 of the Accomplishment Instructions of British Aircraft Corporation Model BAC 1-11 Service Bulletin 49-PM 5217, or an FAA-approved equivalent. (b) If the fuel leakage rate exceeds one drop per minute, prior to further use of the APU, rectify the leakage, drain and refill the oil system with fresh oil, and thereafter continue the inspections required by paragraph (a) of this AD. (c) Upon the request of an operator, the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO New York, N.Y. 09667, may adjust the repetitive inspection intervals specified in paragraph (a) of this AD if the request contains substantiating data to justify the change. This amendment becomes effective August 5, 1977.
98-15-09: This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A320-111 and -211 series airplanes. This action requires repetitive inspections to detect fatigue cracking of the frames of the sliding windows in the cockpit, and repair, if necessary. This amendment is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. The actions specified in this AD are intended to detect and correct fatigue cracking of the frames of the sliding windows in the cockpit, which could result in reduced structural integrity of the pressure vessel of the fuselage of the airplane.
2009-26-02: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: It has been found the occurrence of engine anti-ice system valve failure, where the valve spring seat has broken and obstructed the anti-ice system venturi tube. * * * Therefore, should the aircraft encounter icing conditions, ice may accrete in the engine inlet lip and be ingested through the air inlet, resulting in possible engine damage and flame-out. We are issuing this AD to require actions to correct the unsafe condition on these products.
97-19-11: This amendment supersedes an existing airworthiness directive (AD), applicable to certain Bombardier Model CL-600-2B19 series airplanes, that currently requires revising the Limitations Section of the Airplane Flight Manual (AFM) to provide the flight crew with procedures to check the travel range of the aileron. That AD also requires inspection for damage of the shear pins of the aileron flutter damper and aileron hinge fittings, and various follow-on actions. This amendment adds a requirement for accomplishment of an installation that eliminates the need for the AFM revision. This amendment also adds airplanes to the applicability of the existing AD. This amendment is prompted by reports of failure of shear pins in the aileron flutter damper. The actions specified by this AD are intended to prevent damage to the aileron hinge fittings due to failed shear pins, and consequent reduced controllability of the airplane.
93-22-08: 93-22-08 JETSTREAM AIRCRAFT, LIMITED: Amendment 39-8732. Docket 93-NM-176-AD. ` Applicability: All Model 4101 airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent high current arcing and overheating of certain earth post assemblies and their associated earth (ground) wires, thus creating an in-flight fire hazard, accomplish the following: (a) Within 25 hours time-in-service after the effective date of this AD, conduct a visual and hands-on inspection to detect discrepancies (i.e., overheating, looseness, etc.) of earth post EP2 (left) and earth post EP4 (right) and their attached earth cables, in accordance with the Accomplishment Instructions of Jetstream Series 4100 Alert Service Bulletin J41-A24-012, Revision 1, dated September 13, 1993. (1) If no discrepancy is detected, no further action is required. (2) If any discrepancy is detected, prior to further flight, replace the discrepant earth post with a new earth post and earth cables in accordance with paragraph B. of the Accomplishment Instructions of Jetstream Series 4100 Alert Service Bulletin J41-A24-012, Revision 1, dated September 13, 1993. (b) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (c) 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.(d) The inspections and replacement shall be done in accordance with Jetstream Series 4100 Alert Service Bulletin J41-A24-012, Revision 1, dated September 13, 1993, which contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1, 3, 6 1 September 13, 1993 2, 4-5, 7, Original September 8, 1993 8, 9 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 Jetstream Aircraft, Inc., P.O. Box 16029, Dulles International Airport, Washington, DC 20041-6029. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on December 3, 1993.
77-15-04: 77-15-04 ENSTROM: Amendment 39-2973. Applies to Enstrom Models F28C and 280C helicopters with wide chord (4.4 inch) tail rotor blades certificated in all categories. Before further flight perform a dye penetrant inspection around the circular hub including the arm base of the pitch link retainer assembly P/N 28-16320 unless already accomplished in the last ten hours time in service. Within ten (10) hours time in service after the receipt of this airmail letter, unless already accomplished, replace the wide chord tail rotor pitch link assembly P/N 28- 16320 and two (2) guide bolts P/N 28-16307 with a new wide chord tail rotor pitch link retainer assembly P/N 28-16325 and two (2) guide bolts P/N 28-16324. Enstrom Service Directive Bulletin Number 0040 pertains to this same subject. This amendment is effective July 26, 1977, and was effective immediately for all recipients of airmail letters dated June 15, 1977 which contained this amendment.
2004-13-02: This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, -200B, and -200F series airplanes. This action requires initial and repetitive inspections to find discrepancies in the upper and lower skins of the fuselage lap joints, and repair if necessary. This action is necessary to find and fix such discrepancies, which could result in sudden fracture and failure of a lap joint and rapid in-flight decompression of the airplane fuselage. This action is intended to address the identified unsafe condition.
76-13-04: 76-13-04 MCDONNELL DOUGLAS: Amendment 39-2652. Applies to Douglas Model DC-10-10 and -30 series airplanes, certificated in all categories, incorporating lower galleys. \n\n\tCompliance required within the next 3000 hours' time in service after the effective date of this AD, unless already accomplished. \n\n\tTo provide better access to the portable oxygen units in the lower galley, relocate the two portable oxygen units originally installed outboard of the forward escape ladder in the lower galley to the port side of the forward bulkhead and adjacent to the attendant seats. Additional installations and/or other locations may be approved by the Chief, Aircraft Engineering Division, FAA Western Region. \n\n\tSpecial flight permits may be issued per FAR's 27.197 and 21.199 to operate airplanes to a base for the accomplishment of this AD. \n\n\tThis amendment becomes effective August 3, 1976.
95-09-06: This amendment adopts a new airworthiness directive (AD), applicable to Bell Helicopter Textron, Inc. (BHTI) Model 206A, 206B, 206L, 206L-1, and 206L-3 helicopters, that requires installing a protective mechanical fuel valve switch guard on the fuel valve switch. This amendment is prompted by reports of airmen inadvertently placing the fuel valve switch to the "OFF" position. The actions specified by this AD are intended to prevent the fuel valve switch from being inadvertently placed in the "OFF" position, which could result in an engine failure and a subsequent power-off landing.
93-20-06: 93-20-06 AYRES CORPORATION: Amendment 39-8714; Docket No. 93-CE-31-AD. Applicability: The following model and serial number airplanes, certificated in any category: Models Serial Numbers S2D all serial numbers S2R 5000 through 5099, 1380R, and 1416R through 2582R S2R-R1340 R1340-001 through R1340-028 (with or without DC suffix) S2R-R3S R3S-001 through R3S-011 (with or without DC suffix) S2R-R1820 R1820-001 through R1820-035 (with or without DC suffix) S2R-T11 T11-001 through T11-005 (with or without DC suffix) S2R-T15 T15-001 through T15-029 (with or without DC suffix); and T27-001 through T27-029 (with or without DC suffix) S2R-T34 6000 through 6049, T34-001 through T34-143, T34-145, T34-147 through T34-167, T34-170, T34-171, and T34-180 (with or without DC suffix); and T41-001 through T41-143, T41-145, T41-147 through T41-167, T41-170, T41-171, and T41-180 (with or without DC suffix) S2R-T45 T45-001 (with or without DC suffix) Compliance: Required as indicated, unless already accomplished. NOTE 1: The compliance times specified in this AD take precedence over those referenced in Ayres Service Bulletin (SB) No. SB-AG-33, dated February 24, 1993. To prevent structural damage to the wing caused by damaged aluminum outboard wing huckbolts, which could result in loss of control of the airplane, accomplish the following: (a) Within the next 50 hours time-in-service after the effective date of this AD, inspect the existing aluminum outboard wing huckbolts for cracks, shearing, or fatigue in accordance with the ACCOMPLISHMENT INSTRUCTIONS: I. Inspection, section of Ayres SB No. SB-AG-33, dated February 24, 1993. (1) If sheared, cracked, or fatigued aluminum outboard wing huckbolts are found, prior to further flight, replace the last 13 vertical rows of aluminum huckbolts with NAS 1103 steel bolts or with steel huckbolts in accordance with the ACCOMPLISHMENT INSTRUCTIONS: II. Repair, section of Ayres SB No. SB-AG-33, dated February 24, 1993. (2) If no cracked, sheared, or fatigued huckbolts are found, reinspect at intervals not to exceed 100 hours TIS. Accomplish no more than five 100-hour inspection repetitions before replacing the huckbolts as required by paragraph (b) of this AD. NOTE 2: The FAA established the compliance times of the initial inspection and the repetitive inspections to coincide with the replacement compliance time specified in paragraph (b) of this AD. (b) Within the next 650 hours TIS after the effective date of this AD, unless already accomplished in accordance with paragraph (a)(1) of this AD, replace the last 13 vertical rows of aluminum huckbolts with NAS 1103 steel bolts or with steel huckbolts in accordance with the ACCOMPLISHMENT INSTRUCTIONS: II. Repair, section of Ayres SB No. SB-AG-33, dated February 24, 1993. NOTE 3: The FAA established the replacement compliance time by estimating airplane operation rates in order to allow the operator the opportunity to accomplish the action during the next annual maintenance inspection. (c) Replacing the huckbolts as specified in paragraph (b) of this AD eliminates the inspection requirement of this AD and may be accomplished prior to 650 hours TIS. (d) 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. (e) An alternative method of compliance or adjustment of the initial or repetitive compliance times that provides an equivalent level of safety may be approved by the Manager, Atlanta Aircraft Certification Office, 1669 Phoenix Parkway, Suite 210C, Atlanta, Georgia 30349. The request shall be forwarded through an appropriate FAA Maintenance Inspector, who may add comments and then send it to the Manager, Atlanta Aircraft Certification Office. NOTE 4: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Atlanta Aircraft Certification Office. (f) The inspection and replacement required by this AD shall be done in accordance with Ayres Service Bulletin No. SB-AG-33, dated February 24, 1993. 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 the Ayres Corporation, P.O. Box 3090, Albany, Georgia 31708. Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment (39-8714) becomes effective on December 3, 1993.
2009-24-04: The FAA is adopting a new airworthiness directive (AD) for Rolls-Royce Corporation (RRC) AE 3007A1/1, AE 3007A1/3, AE 3007A1, AE 3007A1E, AE 3007A1P, AE 3007A3, AE 3007C, and AE 3007C1 turbofan engines with a fan spinner part number (P/N) 23070964 or P/N 23078783, installed. This AD requires replacement of the fan spinner. This AD results from a report of a fan spinner releasing from an AE 3007A turbofan engine, during flight. We are issuing this AD to prevent the fan spinner from releasing, which could result in injury, damage to the engine, and damage to the airplane.
92-27-01: 92-27-01 AEROSPATIALE: Amendment 39-8434. Docket No. 92-NM-147-AD. Applicability: All Model ATR42 and ATR72 series airplanes, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent increased risk of injury to the passengers and crew members in the event of a fire within the airplane cabin, accomplish the following: (a) For Model ATR42 series airplanes: Within 2 years after the effective date of this AD, remove the door linings and perform a general visual inspection to determine the date of their manufacture, in accordance with Aerospatiale Service Bulletin ATR42-25-0084, dated April 10, 1992. (1) If the door linings were manufactured prior to January 15, 1990, prior to further flight, replace them with linings manufactured after January 15, 1990, in accordance with Aerospatiale Service Bulletin ATR42-25-0075, dated September 4, 1991. (2) If the door linings were manufactured on or after January 15, 1990, reinstall the linings. No further action is required by this AD. (b) For Model ATR72 series airplanes: Within 2 years after the effective date of this AD, remove the door linings and door posts and perform a general visual inspection to determine the date of their manufacture, in accordance with Aerospatiale Service Bulletin ATR72-25-1025, Revision 1, dated May 18, 1992. (1) If the door linings or door posts were manufactured prior to January 15, 1990, prior to further flight, replace them with linings or posts manufactured after January 15, 1990, in accordance with ATR72-25-1020, dated September 4, 1991. (2) If the door linings or door posts were manufactured on or after January 15, 1990, reinstall the linings or posts. No further action is required by this AD. (c) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) 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. (e) The inspections and replacements shall be done in accordance with Aerospatiale Service Bulletin ATR42-25-0084, dated April 10, 1992; Aerospatiale Service Bulletin ATR42-25- 0075, dated September 4, 1991; Aerospatiale Service Bulletin ATR72-25-1025, Revision 1, dated May 18, 1992; or Aerospatiale Service Bulletin ATR72-25-1020, dated September 4, 1991; as applicable. Aerospatiale Service Bulletin ATR72-25-1025, Revision 1, dated May 18, 1992, contains the following list of effective pages: Page Number Revision Level Shown on Page Date Shown on Page 1 1 May 18, 1992 2-9 Original April 10, 1992 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on January 22, 1993.
91-16-07: 91-16-07 BRITISH AEROSPACE: Amendment 39-7097. Docket No. 91-NM-79-AD. Applicability: Model ATP series airplanes, equipped with Smiths Industries Altimeter Repeater Units, Part Number 1205AM1, certificated in any category. Compliance: Required within 120 days after the effective date of this AD, unless previously accomplished. To ensure the pilot receives accurate altitude data, accomplish the following: A. Install a hardened knobshaft, Part Number AM10588, in place of Part Number AM10454, and remount the microswitch (Smiths Industries Modification No. 02), in accordance with British Aerospace Service Bulletin ATP-34-40, dated October 20, 1990. NOTE: The British Aerospace service bulletin references Smiths Industries Service Bulletin 1205AM-34-756 for additional instructions. B. 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. C. 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. D. The modification requirement shall be done in accordance with British Aerospace Service Bulletin ATP-34-40, dated October 20, 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 British Aerospace, PLC, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. 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 (39-7097, AD 91-16-07) becomes effective on September 11, 1991.
92-19-12: 92-19-12 LEARJET (FORMERLY GATES LEARJET): Amendment 39-8370. Docket No. 92-NM-111-AD. Applicability: Model 23, 24, 25, 28, 29, 31, 35, and 36 series airplanes, as listed in Learjet Airplane Modification Kit No. AMK 90-5, dated October 11, 1991; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent electrical arcing and an in-flight fire, accomplish the following: (a) Within 30 days after the effective date of this AD, modify the crew oxygen plumbing and map light wires, in accordance with Learjet Airplane Modification Kit AMK No. 90-5, dated October 11, 1991. (b) 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, Wichita Aircraft Certification Office (ACO), ACE-115W, FAA, Small Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector,who may add comments and then send it to the Manager, Wichita ACO. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Wichita ACO. (c) 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. (d) The modification shall be done in accordance with Learjet Airplane Modification Kit AMK No. 90-5, dated October 11, 1991. 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 Learjet Corporation, Customer Services, P.O. Box 7707, Wichita, Kansas 67277-7707. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (e) This amendment becomes effective on November 17, 1992.
93-14-07: 93-14-07 AEROSPATIALE: Amendment 39-8631. Docket 93-NM-06-AD. Applicability: Model ATR72-100 and -200 series airplanes; on which either Modification 03616, as described in Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992, or Modification 03584 have not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent loss of structural strength of the floor beam and pressure plate, or loss of cabin pressurization, accomplish the following: (a) Prior to the accumulation of 1,000 total flight cycles, or within the next 30 days after the effective date of this AD, whichever occurs later, perform a detailed visual inspection to detect cracks of the floor beam at frame 26 of the fuselage in the buttock line 0 area, in accordance with Aerospatiale Service Bulletin ATR72-53-1026, Revision 1, dated January 22, 1993. (1) If no crack is found, accomplish either paragraph (a)(1)(i) or (a)(1)(ii) of this AD: (i) Thereafter, at intervals not to exceed 1,000 flight cycles, repeat the detailed visual inspection. (ii) Within the next 1,000 flight cycles, install Modification 03616 in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992. No further action is required by this AD. (2) If a single crack is found that is less than 65 millimeters (mm) in length, accomplish either paragraph (a)(2)(i) or (a)(2)(ii) of this AD. (i) Thereafter, at intervals not to exceed 750 flight cycles, repeat the detailed visual inspection. (ii) Within the next 750 flight cycles after crack discovery, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (3) If a single crack is found that is equal to or greater than 65 mm but less than 80 mm in length: Within the next 250 flight cycles after crack discovery, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (4) If a single crack is found that is equal to or greater than 80 mm in length: Prior to further flight, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (5) If two or more cracks are found: Prior to further flight, repair the cracks in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (b) Prior to the accumulation of 1,000 total flight cycles, or within the next 30 days after the effective date of this AD, whichever occurs later, perform a high frequency eddy current (HFEC) inspection of the pressure plate forward and aft of the floor beam at frame 26 of the fuselage at buttock line 0, in accordance with Aerospatiale Service Bulletin ATR72-53-1026, Revision 1, dated January 22, 1993. (1) If no crack is found, accomplish either paragraph (b)(1)(i) or (b)(1)(ii) of this AD: (i) Thereafter, at intervals not to exceed 1,000 flight cycles, repeat the HFEC inspection. (ii) Within the next 1,000 flight cycles, install Modification 03616 in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992. No further action is required by this AD. (2) If a single crack is found that is less than 65 millimeters (mm) in length, accomplish either paragraph (b)(2)(i) or (b)(2)(ii) of this AD: (i) Thereafter, at intervals not to exceed 500 flight cycles, repeat the HFEC inspection. (ii) Within the next 500 flight cycles after crack discovery, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (3) If a single crack is found that is equal to or greater than 65 mm but less than 80 mm in length: Withinthe next 250 flight cycles after crack discovery, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (4) If a single crack is found that is equal to or greater than 80 mm in length: Prior to further flight, repair the crack in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (5) If two or more cracks are found: Prior to further flight, repair the cracks in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. No further action is required by this AD. (c) Within 6 months after the effective date of this AD, if no crack is present, install Modification 03616 in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992; or, if any crack is present, repair in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. (d) Installation of Modification 03616 in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992; or repair in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993; constitutes terminating action for the repetitive detailed visual inspections of the floor beam and repetitive HFEC inspections of the pressure plate required by 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (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) The inspection shall be done in accordance with Aerospatiale Service Bulletin ATR72-53-1026, Revision 1, dated January 22, 1993. The installation shall be done in accordance with Aerospatiale Service Bulletin ATR72-53-1027, dated December 18, 1992. The repair shall be done in accordance with Aerospatiale Service Bulletin ATR72-53-1028, dated January 18, 1993. 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 Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (h) This amendment becomes effective on September 10, 1993.
93-15-05: 93-15-05 AIRBUS INDUSTRIE: Amendment 39-8651. Docket 93-NM-117-AD. Applicability: Model A320 series airplanes on which Airbus Industrie Modification 20856 or Airbus Industrie Service Bulletin A320-32-1090 has been accomplished, and on which Airbus Industrie Modification 23597 or Airbus Industrie Service Bulletin A320-32-1114 has not been accomplished; certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent reduced braking performance, accomplish the following: (a) Within 30 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) by inserting a copy of Airbus Industrie A320 Flight Manual Temporary Revision 9.99.99/89, Issue 2, dated December 16, 1992, in the AFM. (b) Accomplishment of Airbus Industrie Modification 23597 or Airbus Industrie Service Bulletin A320-32-1114 and replacement of Airbus Industrie A320 Flight Manual Temporary Revision 9.99.99/89, Issue 2, dated December 16, 1992, with Airbus Industrie A320 Flight Manual Temporary Revision 9.99.99/89, Issue 3, dated February 8, 1993, in the AFM constitutes terminating action for the requirements of paragraph (a) of this AD. (c) 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, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Standardization Branch, ANM-113. NOTE: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Standardization Branch, ANM-113. (d) 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. (e) The AFM revision shall be accomplished in accordance with Airbus Industrie A320 Flight Manual Temporary Revision 9.99.99/89, Issue 2, dated December 16, 1992, which contains the following list of effective pages: Page Number Issue Level Shown on Page Date Shown on Page 1 2 December 16, 1992 2 Original November 3, 1992 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, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (f) This amendment becomes effective on August 18, 1993.
47-51-14: 47-51-14 SIKORSKY: Applies to Models YR-6A, R-6A, HOS-1 Helicopters. Compliance required at each removal and replacement of the power takeoff assembly. In order to prevent failure of the pinion and ring gears in the main gearbox due to improper installation of the power takeoff assembly, the following teardown, inspection, and assembly procedure should be followed: (a) Disconnect and remove the front end of the intermediate drive shaft. (b) Remove the cotter pin and nut in the center of the spline coupling, P/N S-635104, and remove the spline coupling with attached brake disc. (c) Check the backlash in the power takeoff gears. This should be 0.003 to 0.005 inch between the ring gear and pinion. (d) Remove the five retaining nuts and washers securing the power takeoff to the main gearbox lower housing. (e) Using a fiber mallet, for starting, remove the power takeoff. CAUTION: Do not use a screwdriver or pry bar on the mating surfaces, as the slightest deformation of the surfaces may cause gear failure. (f) Inspect the shims, P/N S-635117, and gasket, P/N S-635115, for dents and tears. Only shims and gaskets in perfect condition should be considered serviceable. Also, the mating surfaces of the housings should be free from rough spots or tool deformations. (g) With a micrometer, measure the total thickness of the shim. If it is necessary to replace a shim, and the backlash was within limits, the replacement shim must have the same total thickness as the parts removed. (h) Lightly coat with Prussian blue the teeth of the power takeoff pinion. (i) Place gasket P/N S-635115 in gasket recess. (j) Replace the shims over the five studs in the lower case of the main gearbox, install the power takeoff housing assembly, and secure the five washers and nuts. (k) Check the backlash between the ring gear and pinion, which must be between 0.003 to 0.005 inch. (l) After the power takeoff has been fastened securely in place, the gearbox must be operated by hand by turning the end of the pinion shaft protruding from the power takeoff. After a few revolutions, remove the power takeoff and check the tooth pattern. The correct tooth pattern is shown in Figure 5. The necessary adjustment for proper tooth pattern and backlash should be accomplished by shimmying with power takeoff housing shims. Shims are to provide adjustments for both mounting distance of ring gear and pinion and also tooth pattern. (m) When the proper tooth pattern and backlash have been obtained, install the power takeoff and securely tighten retaining nuts. (n) Replace the spline coupling with brake disc attached and secure with washer, nut, and cotter pin. (o) Reassemble the front end of the intermediate drive shaft. (Similar instructions are contained in AAF Technical Order No. 01-230 of HC-16, dated March 6, 1946, and in Bureau of Aeronautics Aircraft Bulletin No. 6 dated March 28, 1947.)