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78-11-01: 78-11-01 BEECH: Amendment 39-3220 as amended by Amendment 39-3277 is further amended by Amendment 39-3413. Applies to E50, F50, G50, H50, J50, 65, A65, A65-8200, 65- 80, 65-A80, 65-A80-8800, 65-B80, 65-88 and 70 model airplanes certified in all categories except those modified in accordance with STCs SA444SW or SA587SW. COMPLIANCE: Required as indicated unless already accomplished. To reduce the possibility of powerplant fire occurrence and improve powerplant fire containment and detection capabilities, accomplish the following: A) Within the next 25 hours time-in-service after June 1, 1978, install in the existing Airplane Flight Manual, the temporary airplane Flight Manual Supplement included in this AD as Figure 1, or, Beech Aircraft Company Airplane Flight Manual Supplement P/N 50-590211-31 dated May 29, 1978 or subsequent revision. B) Within the next 100 hours time-in-service after June 1, 1978, except that this compliance time may be extended to 200 hourstime-in-service if the inspection of components forward of the firewall required by AD 77-25-01 is accomplished at intervals no greater than 50 hours time-in-service during this compliance time extension. 1) Replace existing flexible fuel, oil, hydraulic, and fuel or oil vapor carrying hose assemblies except engine breather and drain lines in the engine compartment with equivalent length and diameter hoses having strength and fire resistance qualities meeting FAA Technical Standard Order C53A, Type C or D or as specified below. Hose assemblies fabricated of Stratoflex Type 111 or 130 hose covered by fire-resistant sleeve, Stratoflex Type 2650 or 2607 or Aeroquip hose Type 303 covered with fire-resistant sleeve Type AE102 or 624 or hose specified in Beechcraft Service Instructions No. 0999 or later approved revisions, or an FAA- approved equivalent are acceptable except as noted below. (Pressure test the hose assemblies in accordance with industry practice.) On airplanes having serial numbers LC-157 through LC-335, LB-1 through LB-35, and LD-135 through LD-512, replace the main oil supply hose running from the firewall to the engine with a Stratoflex Part No. 156F001-16D0200 hose assembly or Aeroquip 620100-16-0200 hose assembly or an FAA-approved equivalent. On the Model 88 series airplanes, fabricate the hose from the engine hydraulic pump "oil out" to the firewall using high pressure type hose. Stratoflex Type 112 or Aeroquip Type 309 or FAA-approved equivalent is acceptable. Subject only these hoses to a proof pressure test of 7000 PSI and install applicable hose manufacturer's fire sleeves of types noted above. Stratoflex Type 111 or 130 hose or Aeroquip Type 303 hose with appropriate manufacturer's fire sleeve as noted above or hose specified in Beechcraft Service Instructions No. 0999 or later approved revisions, or an FAA-approved equivalent are acceptable for all other pressurization system hoses. Engine induction system hoses and vacuum system hoses are not included in the requirements of this AD. Use old hoses as a pattern when fabricating new hoses. Caution should be exercised to assure end fittings on new hoses are equivalent to old hose end fittings. Install hoses observing manufacturer's torque limits. The torque chart contained in Beechcraft Service Instructions No. 0999 or later approved revisions list acceptable limits. Apply paint or torque putty to fittings after tightening. 2) On airplanes having engines with Bendix fuel injection system, after changing all engine and installation fuel system hoses but prior to connecting the hose at the fuel injector nozzle located at the top of the induction housing, cap this hose at the nozzle end, select main tanks, turn main boost pumps ON, place mixture controls in rich position, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck prior to installing hose on nozzle fittings. 3) On airplanes otherthan those specified in Paragraph B(2) above, after changing all installation fuel system hoses, with mixture control in "cut off", select main tanks, turn main boost pumps ON, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck. 4) After determining that no fuel is trapped in the induction system, conduct the runup specified in Figure 1 and inspect all hoses and fittings for signs of fuel or oil leakage. C) On or before January 31, 1979 install continuous type fire detector systems in the engine compartment and wheel wells in accordance with Beech Service Kit 80-9010. NOTE: The compliance date for this paragraph was established on the basis of the most accelerated schedule the vendors of the detector components can meet and the estimated number of active airplanes of the affected models. The FAA recommends that every owner place an order for the necessary modification kit as early as possible. D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region. Beechcraft Service Instructions No. 0999 or later approved revisions referenced herein covers the subject matter of this AD. Figure 1 TEMPORARY AIRPLANE FLIGHT MANUAL SUPPLEMENT FOR BEECH MODEL 50 SERIES, 65 SERIES A65 SERIES AND 70 AIRPLANES WITH RECIPROCATING ENGINES (AD 78-11-01 requires this supplement to remain in the below designated airplane flight manual until replaced by Beech Aircraft Company Flight Manual Supplement P/N 50-590211-31 dated May 29, 1978, or later approved revisions.) Model_____________ N____________ S/N ______________ In addition to the presently specified preflight procedures, prior to the first flight of each day accomplish the following. 1. Start both engines and operate at 1500 RPM. After the oil pressures stabilize, shut down the engines using the mixture control. 2. Open thecowl doors on both sides of the engines and check all engine compartment fluid hoses and fittings for indications of fluid (fuel or oil) leakage Check the wheel wells for these same conditions using a flashlight or supplemental light as necessary to provide adequate illumination of the area. 3. Correct any leak detected and secure cowl doors. Amendment 39-3220 became effective June 1, 1978. Amendment 39-3277 became effective August 17, 1978. This amendment 39-3413 becomes effective February 6, 1979.
94-14-20 R1: This amendment revises an existing airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76A helicopters. That AD currently requires a one-time inspection of the tail rotor blade (blade) spar elliptical centering plug (centering plug) for disbonding and the addition of a retaining pad on the pitch change shaft between the output tail rotor gearbox flange and the inboard tail rotor spar. This amendment contains the same requirements as the existing AD but clarifies that the 500-hour time-in-service (TIS) repetitive inspections, which could cause inadvertent damage, are not required. This AD also incorporates by reference a revised alert service bulletin (ASB) that does not include the 500-hour TIS repetitive inspections. This amendment is prompted by operator confusion about whether the current AD continues to require the 500- hour TIS repetitive inspections. The actions specified by this AD are intended to verify that the FAA has determined that the500-hour TIS repetitive inspections are not required to prevent the centering plug from disbonding and moving out of position, loss of tail rotor control, and subsequent loss of control of the helicopter.
74-12-08: 74-12-08 AIRESEARCH MANUFACTURING COMPANY of ARIZONA: Amendment 39-1862. Applies to Model TSCP700-5 Auxiliary Power Units installed in, but not limited to, Airbus Industries Model A300B aircraft certificated in all categories. Compliance required as indicated. (a) For APU's with less than 1500 operating cycles on the effective date of this AD, inspect, prior to any further in-flight operation, unless already accomplished, the fuel control differential pressure regulator housing, P/N 977320-1 or -2, for minimum dimensions and cracks per paragraphs 2.B.(2) and (3) of AiResearch Alert Service Bulletin 969900-49-A3644, dated May 14, 1974, or later FAA-approved revisions. Re-work parts, if necessary, per paragraph 2.B.(4). Housings which meet the prescribed minimum dimensions, or which are reworked to meet these dimensions per paragraph 2.B.(4) shall be re-identified as P/N 977320-4. Housings not meeting these dimensional requirements shall be rendered unserviceable and replaced with serviceable P/N 977320-4 housings. Housings which meet inspection and dimensional requirements may be continued in service up to a maximum of 1500 operating cycles. Note: For the purpose of this AD, an APU operating cycle is any operation consisting of a start and shut-down. The number of cycles may be determined by actual count, or, subject to acceptance by the assigned FAA Maintenance Inspector, may be calculated by dividing the fuel control assembly time in service by the operator's fleet average APU operating time per APU operating cycle. (b) For all APU's with 1,500 or more operating cycles in service on the effective date of this AD, inspect per (a), above, prior to further in-flight operation, unless already accomplished, and, in addition thereto, and prior to further in-flight operation, modify the fuel control assembly per (c), below. (c) Before exceeding 1500 operational cycles in service, inspect the fuel control differential pressure regulator body per paragraph 2.B.(2) and modify the fuel control assembly in accordance with paragraph 2.C. of AiResearch Service Bulletin 969900-49-A3644, dated May 14, 1974, or later FAA-approved revisions. Re-identify fuel control assembly per paragraph 2.D. of the referenced service bulletin. (d) Within 3000 operating cycles in service after the accomplishment of paragraph (c), above, and at intervals not to exceed 3000 operating cycles in service thereafter, perform the inspections as defined in paragraph 2.B.(2) of AiResearch Service Bulletin 969900-49-A3644, dated May 14, 1974, or later FAA-approved revisions. (e) The inspections prescribed in paragraph (d), above, may be discontinued when the fuel control differential pressure regulator P/N 977320-4 is replaced with a housing, P/N 977656-1. (f) Equivalent procedures may be approved by the Chief, Aircraft Engineering Division, FAA Western Region, upon submission of adequate substantiation data. This amendment becomes effective June 10, 1974.
77-10-07: 77-10-07 BELL HELICOPTER TEXTRON: Amendment 39-2900. Applies to Model 205A-1 helicopters, Serial Numbers 30001 through 30232, certificated in all categories. For helicopters certificated and operated pursuant to Part 133 of the FARs (Class B rotorcraft-load combination or Class C rotorcraft-load combinations as defined by Part 1 of the FARs), compliance is required within the next 100 hours cumulative time in service involving external load combinations as defined above, or 300 hours total time in service, whichever comes first, after the effective date of this Airworthiness Directive (AD), unless previously accomplished. For standard category helicopters not approved for external load operations as defined above, compliance is required within the next 300 hours time in service after the effective date of this AD, unless previously accomplished. To prevent failure of the engine-to-transmission drive couplings due to excessive angularity under high loading conditions,adjust the engine-to-transmission alignment as described below: (a) Remove the engine-to-transmission driveshaft assembly, P/N's 205-040-004-3, - 11, or -17, in accordance with instructions in the appropriate maintenance and overhaul manuals. (b) Using instructions and special tools prescribed by the maintenance and overhaul manuals, establish the engine-to-transmission alignment prescribed by the manual except as follows: (1) Index the target plate inner scale to 8.0 (instead of 3.5) and index the target plate outer scale to 35.6 (instead of 1.75). NOTE: Transmission position must be adjusted and leveled to maintenance manual specifications. Engine position adjustment procedures must follow maintenance manual instructions. (2) Establish angularity as follows: Install dial indicator in accordance with instructions in the maintenance manual at 2.5 inch radius. Read zero at 12 o'clock position; read +0.030 + 0.004 at 6 o'clock position. Reset dial indicatorto zero at the 3 o'clock position; read +0.006 + 0.004 at 9 o'clock position. Plus reading on dial indicator means that flange on transmission is closer to flange on engine. (c) Shim engine support fittings to obtain required alignment. If total laminated shim thickness (P/N 205-060-137-1 or 205-060-138-1), required under any engine support fitting, exceeds 0.188 inches, fabricate a plate of 2024-T4 aluminum alloy 0.100 thick, same outside dimensions as shim stock, and structurally bond the plate to the engine service deck with EC 934. Total thickness of shims and plate under any engine mount fitting must not exceed 0.288 inches. Verify that the engine support fittings are reinstalled with the same fore and aft orientation as before. (d) Interference between the engine and the aft upper firewall at the 9 o'clock position (looking forward) may result with this realignment. If this condition occurs, accomplish the following: Remove the aft upper firewall assembly P/N 205-060-909-27 and disassemble by removing the sixteen (16) screws. Remove the aft section of the firewall web P/N 204-060-909-13 and enlarge the sixteen (16) holes by drilling to 5/16 inch. Deburr the drilled holes. Reassemble the firewall assembly using P/N AN970-3 washers over the enlarged holes and under the 16 screw heads. (e) Check engine deck fittings screws and bolts for proper length and thread engagement. (f) Check fuel control and governor linkage for proper rigging and cushion. (g) Reinstall the driveshaft assembly. Reinstall transmission 5th mount assembly. Follow maintenance manual instructions for details of reinstallation of access panels, firewall attachments, and related cleanup, as required. Equivalent means of compliance with the modifications prescribed by this AD may be approved by the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, Post Office Box 1689, Fort Worth, Texas, 76101. Upon request of the operator, an FAA maintenance inspector, subject to prior approval of the Chief, Engineering and Manufacturing Branch, Flight Standards Division, Southwest Region, Federal Aviation Administration, may adjust the compliance time prescribed by this AD, if the request contains substantiating data to justify the increase for that operator. This amendment becomes effective May 18, 1977.
87-16-10: 87-16-10 SHORT BROTHERS PLC: Amendment 39-5699. Applies to Model SD3-60 airplanes, serial numbers SH3601 through SH3691 and SH3694, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent loss of the structural integrity of the horizontal stabilizer accomplish the following: A. Visually inspect, in accordance with the schedule listed below, the forward face of the rear spar web and the aft face of the front spar web for cracks between fuselage attach fitting at 12.5" left and right of the airplane center line, in accordance with Short Brothers Model SD3-60 Service Bulletin SD360-55-11, Revision 3, dated April 28, 1987. 1. For airplanes serial numbers SH3680 through SH3691 and SH3694, and airplanes which have used only 15 degrees flap take-off since before or upon reaching 5000 flights, inspection is required within the next 100 flights or prior to the accumulation of 12,000 flights, whichever occurs later. Repeat the inspection at intervals not to exceed 1,500 flights. 2. For all other airplanes, inspection is required within the next 100 flights or prior to the accumulation of 8,000 flights, whichever occurs later. Repeat the inspection at intervals not to exceed 1,000 flights. B. If cracks are found, prior to further flight, modify by strengthening the horizontal stabilizer in accordance with Short Brothers Model SD3-60 Service Bulletin SD360-55-12, dated April 1986. C. The repetitive inspections required by paragraph A., above, may be terminated following completion of the modification described in Short Brothers Model SD3-60 Service Bulletin SD360-55-12, dated April 1986. D. 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. E. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspections and/or modifications required by 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 Short Brothers Aircraft, 2011 Crystal Drive, Suite 713, Arlington, Virginia 22202-3702. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment becomes effective September 10, 1987.
2016-13-14: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model DHC-8-400 series airplanes. This AD requires an inspection to determine if certain left and right main landing gear (MLG) retract actuator rod ends are installed and repetitive liquid penetrant inspections (LPIs) of affected left and right MLG retract actuator rod ends, and corrective actions if necessary. This AD also provides optional terminating action for the inspections. This AD was prompted by a report of cracked MLG retract actuator rod ends. We are issuing this AD to detect and correct fatigue cracking of the left and right MLG retract actuator rod ends, which could lead to left or right MLG collapse.
2016-13-10: We are superseding Airworthiness Directive (AD) 2012-12-04, for certain The Boeing Company Model 737-300, -400, and -500 series airplanes. AD 2012-12-04 required repetitive external detailed inspections and nondestructive inspections to detect cracks in the fuselage skin along the chem-mill steps at stringers S-1 and S-2R, between station (STA) 400 and STA 460, and repair if necessary. This new AD requires a preventive modification of the fuselage skin at crown stringers S-1 and S-2R. This new AD also reduces the inspection threshold for certain airplanes. This AD was prompted by a determination that, for certain airplanes, the skin pockets adjacent to the Air Traffic Control (ATC) antenna are susceptible to widespread fatigue damage. We are issuing this AD to detect and correct fatigue cracking of the fuselage skin panels at the chem-mill steps, which could result in sudden fracture and failure of the fuselage skin panels, and consequent rapid decompression of the airplane.
2001-09-03: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Model A330 series airplanes. This action requires repetitive inspections of the spars, rib, and stringers in the vertical stabilizer spar box for failure of the bonds to the skin, and repair, if necessary. It also requires modification of the vertical stabilizer spar box by installation of fasteners to reinforce the bonds to the skin, which terminates the repetitive inspections. This action is prompted by issuance of mandatory continuing airworthiness information. This action is necessary to prevent failure of the bonds of the vertical stabilizer spar box to the skin, which could lead to reduced structural integrity of the spar box. It is intended to address the identified unsafe condition.
2001-08-15: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce Corporation (formerly Allison Engine Company) AE 3007A, AE 3007A1/1, AE 3007A1/2, AE 3007A1, AE 3007A1/3, AE 3007A1P, and AE 3007A3 turbofan engines. This action requires initial and repetitive inspections for bearing material contamination of the engine oil system. This amendment is prompted by reports of rapid failures of the No. 1 bearing. The actions specified in this AD are intended to detect the rapid failure of the No. 1 bearing, which could result in smoke in the cabin and an uncommanded in-flight engine shutdown.
88-21-05: 88-21-05 PIPER: Amendment 39-6039. Applies to PA-60 series (all serial numbers) airplanes certificated in any category modified per Machen, Inc., Supplemental Type Certification (STC) No. SA980NM. NOTE: STC No. SA980NM pertains to installation of AVCO Lycoming Model TIO-and LTIO-540-J2BD engines. Compliance: Required as indicated, unless previously accomplished. To prevent a possible inflight engine fire, accomplish the following: (a) Within the next 50 hours time-in-service, after the effective date of this AD, and thereafter at every 100 hours time-in-service, inspect, and replace, as necessary, the exhaust systems on both engines in accordance with Machen, Inc. Service Bulletin (SB) No. 66- 018, dated June 5, 1987. (b) The repetitive inspections specified in paragraph (a) are no longer required when the exhaust system has been modified in accordance with Machen, Inc. SB 66-019, dated January 8, 1988. (c) Within the next 50 hours time-in-service, after the effective date of this AD, and thereafter at every 100 hours time-in-service, inspect, and replace as necessary the oil lines on both engines in accordance with Machen, Inc. SB 66-018, dated June 5, 1987. (d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (e) An equivalent means of compliance with this AD may be used if approved by the Manager, Modification Branch, ANM-190S, FAA, Northwest Mountain Region, 17900 Pacific Highway South, C-68966, Seattle, Washington 98168. All persons affected by this directive may obtain copies of the documents referred to herein upon request to Machen, Inc., South 3608 Davison Boulevard, Spokane, Washington 99204 or may examine these documents at the Office of the Assistant Chief Counsel, Room 1558, FAA, 601 East 12th Street, Kansas City, Missouri 64106. This amendment, 39-6039, becomes effective on November 6, 1988.
2016-13-08: We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called Model A300-600 series airplanes). This AD was prompted by a report of cracking of the lower tension bolt area at the rib one junction (both sides) of the lower wing. This AD requires repetitive inspections for cracking of the fasteners and of the fitting around the fastener holes at the frame (FR) 40 lower wing location, and corrective actions if necessary. We are issuing this AD to detect and correct crack initiation of the fittings of the FR40 lower wing locations, which could result in reduced structural integrity of the airplane.
2001-08-12: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Model A340 series airplanes. This action requires repetitive inspections of the pivoting door roller fittings of the upper and lower thrust reversers for cracks, and corrective action, if necessary. This action is prompted by issuance of mandatory continuing airworthiness information by a foreign civil airworthiness authority. This action is intended to detect and correct cracking of the pivoting door roller fittings of the thrust reversers, which could result in failure of the primary locking mechanism of the thrust reversers during flight, leading to reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
87-16-12: 87-16-12 BRITISH AEROSPACE: Amendment 39-5706. Applies to Model BAe-146 airplanes, as listed in British Aerospace BAe-146 Service Bulletin 27-58, Revision 1, dated November 14, 1986, certificated in any category. Compliance is required as indicated, unless previously accomplished. To prevent an unannunciated failure of the stall identification system, accomplish the following: A. Within 14 days or prior to the accumulation of 125 landings, whichever occurs first after the effective date of this AD, inspect the electro/pneumatic solenoid valve to identify the serial number and modification state in accordance with BAe-146 Service Bulletin 27-58, Revision 1, November 14, 1986. If the valve is identified as suspect, accomplish either of the following: 1. Prior to further flight, replace the affected valve with a modified valve identified in accordance with the service bulletin; or 2. Prior to further flight, and thereafter at intervals not to exceed 14 daysor 125 landings, whichever occurs first, functionally test the suspect valve in accordance with the Accomplishment Instructions of the service bulletin. a. Valves found defective must be removed prior to further flight and replaced with modified valves or a serviceable suspect valve. b. The serviceability of suspect replacement valves must be determined by performing the above mentioned functional test upon installation. B. Replacement of suspect valves with modified valves identified in accordance with BAe-146 Service Bulletin 27-58, Revision 1, dated November 14, 1986, constitutes terminating action for the requirements of this AD. 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, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. D. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operateairplanes to a base for the accomplishment of the modification required by 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 British Aerospace, Librarian for Service Bulletins, P.O. Box 17414, Dulles International Airport, Washington, D.C. 20041. This information may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment, 39-5706, becomes effective August 31, 1987.
86-01-04: 86-01-04 HUGHES HELICOPTERS, INC. (Hughes Helicopters): Amendment 39-5187. Applies to Model 369 series helicopters including military Models YOH-6A and OH-6A, certificated in any category, equipped with tail rotor blades Part Numbers (P/N) 369A1613-3,- 7, -501, and -503, Serial Numbers (S/N) 6928 and prior; P/N's 369D21613-11, -41, and -51, S/N's 5144 and prior; P/N 369D21606, S/N's 0077 and prior; P/N 369D21615, S/N's 0480 and prior; and P/N's 421-088-BSC and -3, all serial numbers. Compliance is required within the next 100 hours time in service after the effective date of this AD, unless already accomplished. To prevent the loss of a tail rotor blade tip cap in flight and subsequent loss of tail rotor control, accomplish the following: (a) Remove, inspect, and modify blades in accordance with paragraphs a through g, Part I "PROCEDURE" section of Hughes Service Information Notices (SIN) DN-132.1, EN-21.1, FN-9.1, HN-199.1 dated May 1, 1985, or SIN's DN-129, EN-18,and HN-195 dated August 27, 1984. (b) An alternate method of compliance which provides an equivalent level of safety may be used when approved by the Manager of the Western Aircraft Certification Office, Hawthorne, California. (c) Special flight permits may be issued in accordance with FAR Sections 21.197 and 21.199 to ferry aircraft to a maintenance base in order to comply with the requirements of this AD. 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 McDonnell Douglas Helicopter Company, Centinela Avenue and Teale Street, Culver City, California 90230. These documents also may be examined at the FAA, Southwest Region, Room 158, Building 3B, 4400 Blue Mound Road, Fort Worth, Texas 76106, or at the Western Aircraft Certification Office, 15000 Aviation Boulevard, Hawthorne, California 90250. This amendment supersedes Amendment 39-4940 (49 FR 43046; October 26, 1984), AD 84-18-08. This amendment becomes effective February 14, 1986.
85-25-56 R1: 85-25-56 R1 GENERAL ELECTRIC COMPANY: Telegram issued December 20, 1985, as amended by Amendment 39-5495. Applies to General Electric Company (GE) CF6-50 and -45 series turbofan engines. Compliance is required as indicated, unless already accomplished. To prevent failure of the left hand side seventh stage low pressure turbine (LPT) cooling air manifold tube, which could result in an LPT overtemperature condition and subsequent LPT stage 1 disk rupture, accomplish the following: (a) For those engines not in compliance with the requirements of GE Service Bulletin (SB) 75-54, dated July 19, 1985, or paragraph 2.A. or 2.B. of GE SB 75-46, Revision 3, dated June 8, 1982, comply with paragraphs (1) then (2) below: (1) Accomplish the requirements of paragraphs 2.A.1. and 2.A.2. of GE SB 75-55, dated September 13, 1985, concurrently with the requirements of paragraph 2.A. of GE SB 75-54, or FAA approved equivalents, within 10 flight cycles after the effective date ofthis AD. (2) Accomplish the requirements of paragraph 2. of GE SB 75-55 or FAA approved equivalent, within 60 calendar days of complying with paragraph (1) above. (b) For engines already in compliance with the requirements of GE SB 75-54 or paragraph 2.A. or 2.B. of GE SB 75-46, accomplish the requirements of paragraph 2. of GE SB 75-55 within 60 calendar days after the effective date of this AD. (c) Replace cracked, broken or ruptured left hand side seventh stage LPT cooling air manifold tube and attachment hardware, found during accomplishment of paragraph (a) or (b) above, before further flight. (d) Inspect the left hand side seventh stage LPT cooling air manifold tubes and attachment hardware in accordance with the requirements of paragraphs 2.A., 2.B., 2.C. and 2.D.(4)(b) of GE SB 75-58, dated April 14, 1986, or FAA approved equivalent, within the next 250 flight cycles after the effective date of this AD, and thereafter, at intervals not to exceed 250 flightcycles from the last inspection. (e) Replace or tighten, in accordance with paragraph 2.D. of GE SB 75-58, left hand side seventh stage LPT cooling air system hardware found worn, loose, cracked or broken during accomplishment of paragraph (d) above, prior to further flight. 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. Upon request, an equivalent means of compliance with the requirements of this AD may be approved by the Manager, Engine Certification Office, Aircraft Certification Division, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803. Upon submission of substantiating data by an owner or operator through an FAA maintenance inspector, the Manager, Engine Certification Office, may adjust the compliance time specified in this AD. GE SB's 75-54, dated July 19, 1985; 75-46, Revision 3, dated June 8, 1982; 75-55, dated September 13, 1985; and 75-58, dated April 14, 1986, identified and described in this document, 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, from General Electric Company, 1 Neumann Way, Cincinnati, Ohio 45215. These documents also may be examined at the Office of the Regional Counsel, Federal Aviation Administration, New England Region, 12 New England Executive Park, Burlington, Massachusetts 01803, Rules Docket Number 85-ANE-44, Room 311, between the hours of 8:00 a.m. and 4:30 p.m., Monday through Friday, except Federal holidays. Paragraphs (a), (b), and (c) of this amendment become effective January 5, 1987, as to all persons except those persons to whom paragraphs (a), (b), and (c) of this amendment were made immediately effective by TAD T85-25-56, issued December 20, 1985. Paragraphs (d) and (e)of this amendment become effective January 13, 1987, as to all persons.
2016-13-12: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) BR700-710A1-10, -710A2-20, and -710C4-11 turbofan engines. This AD requires removing the pawl carrier pivot pins, part number (P/N) BRR17117, from service and replacing them with parts eligible for installation. This AD was prompted by a seized low-pressure turbine (LPT) fuel shut-off pawl carrier caused by corrosion of the pawl carrier pivot pin. We are issuing this AD to prevent failure of the fuel shut-off mechanism, which could result in uncontained part release, damage to the engine, and damage to the airplane.
2001-08-18: This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that requires installation of heat shrinkable tubing or application of Peel-Kote on each terminal connection of all cabin lighting switches in the forward and aft cabin electrical service panels. This action is necessary to prevent a short circuit within the cabin electrical service panel due to a foreign object being lodged between the terminals of a cabin light switch. Such a short circuit could result in overheating and damage to light circuits, and consequent smoke and fire in the main cabin of the airplane. This action is intended to address the identified unsafe condition.
87-06-06: 87-06-06 LOCKHEED-CALIFORNIA COMPANY: Amendment 39-5570. Applies to Lockheed Model L-1011-385 series airplanes, certificated in any category. Compliance required as indicated, unless previously accomplished. To prevent engine separation due to broken pylon attach fittings-to-skate-angle bolts, which are cracking because of stress-corrosion, accomplish the following: A. Before accumulating a total of 15,000 hours time-in-service or within the next 3,000 hours time-in-service after the effective date of the AD, whichever occurs later, and thereafter at intervals not to exceed 3,000 hours time-in-service or 15 months, whichever occurs later, accomplish the following: 1. Inspect the pylon attach fittings-to-skate-angle bolts in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA approved revision. 2. If broken bolts are found, before further flight, replace each broken bolt with a new bolt in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA-approved revision. B. Before accumulating a total of 15,000 hours time-in-service or before January 15, 1991, whichever is later, replace all of the pylon attach fittings-to-skate-angle H-11 steel bolts with stress-corrosion resistant MP-35N bolts in accordance with the Accomplishment Instructions in Lockheed Service Bulletin 093-54-049, Revision 1, dated September 25, 1986, or later FAA- approved revision. The inspections required by paragraph A. may be discontinued after paragraph B. has been accomplished. C. Alternate means of compliance which provide an acceptable level of safety may be used when approved by the Manager, Los Angeles Aircraft Certification Office, FAA, Northwest Mountain Region. 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 documents from the manufacturer may obtain copies upon request to Lockheed-California Company, P.O. Box 551, Burbank, California 91520, Attention: Commercial Order Administration, Dept. 65-33, U-33, B-1. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Los Angeles Aircraft Certification Office, 4344 Donald Douglas Drive, Long Beach, California. This Amendment becomes effective April 2, 1987.
2016-13-05: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines. This AD was prompted by an uncontained failure of the high-pressure compressor (HPC) stage 8-10 spool, leading to an airplane fire. This AD requires eddy current inspection (ECI) or ultrasonic inspection (USI) of the HPC stage 8-10 spool and removing from service those parts that fail inspection. We are issuing this AD to prevent failure of the HPC stage 8-10 spool, uncontained rotor release, damage to the engine, and damage to the airplane.
2001-08-10: This amendment adopts a new airworthiness directive (AD) that applies to certain Aerostar Aircraft Corporation (Aerostar) Models PA-60-600, PA-60-601, PA-60-601P, PA-60-602P, and PA-60-700P airplanes. This AD requires you to replace both of the existing main landing gear lower side brace assemblies with parts of improved design. This AD is the result of several reports of cracking of the main landing gear lower side brace at the upper bolt lug discovered on preflight inspection. The actions specified by this AD are intended to correct damage or cracks in the main landing gear lower side brace at the upper bolt lug where the upper and lower side braces connect. This could result in failure of the main landing gear lower side brace. Such failure could lead to loss of control of the airplane.
2016-12-11: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 787-8 airplanes. This AD was prompted by a report that certain center and outboard stowage bin modules were incorrectly installed. This AD requires an inspection of the center and outboard stowage bin modules for missing parts, quick release pins that are not fully engaged, and parts that are installed in incorrect locations; and corrective actions if necessary. We are issuing this AD to detect and correct incorrectly installed center and outboard stowage bin modules that might not remain intact during an emergency landing, resulting in injuries to occupants and interference with airplane evacuation.
2010-22-02: 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: Seven cases of on-ground hydraulic accumulator screw cap/end cap failure have been experienced on CL-600-2B19 aeroplanes, resulting in the loss of the associated hydraulic system and high-energy impact damage to adjacent systems and structure. * * * * * * * * A detailed analysis of the calculated line of trajectory of a failed screw cap/end cap for each of the accumulators has been conducted, resulting in the identification of several areas where systems and/or structural components could potentially be damaged. Although all of the failures to date have occurred on the ground, an in-flight failure affecting such components could potentially have an adverse effect on the controllability of the aeroplane. * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI.
2016-13-04: We are adopting a new airworthiness directive (AD) for certain BRP-Powertrain GmbH & Co KG Rotax 912 F2, 912 F3, 912 F4, 912 S2, 912 S3, 912 S4, 914 F2, 914 F3, and 914 F4 reciprocating engines. This AD requires re-identification of the engine model and concurrent modification of the aircraft to indicate the maximum coolant temperature limit. This AD was prompted by a design change introduced by the manufacturer that relocated the engine cylinder head temperature sensor to a different location and converted it to a coolant temperature sensor. We are issuing this AD to prevent exceeding engine coolant temperature limits, which could result in loss of engine coolant, damage to the engine, and loss of control of the airplane.
2016-12-14: We are adopting a new airworthiness directive (AD) for all Embraer S.A. Model ERJ 170 airplanes; and all Embraer S.A. Model ERJ 190-100 STD, -100 LR, -100 IGW, -200 STD, -200 LR, and -200 IGW airplanes. This AD was prompted by reports of cracks in certain engine low-stage bleed check valves. This AD requires replacing the air management system (AMS) controller operation program of the AMS controller processor boards, and replacing the current low-stage bleed check valve and associated seals. We are issuing this AD to prevent failure of the low-stage bleed check valve; simultaneous failures of both low-stage bleed check valves could result in a dual engine in- flight shutdown.
74-22-04: 74-22-04 TELEDYNE CONTINENTAL MOTORS: Amendment 39-1998. Applies to TCM Model 6-285- B engines with engine serial numbers 700000 through 700095. Compliance required within the next 25 hours time in service after the effective date of this AD unless already accomplished. Inspect the crankcase main bearing oil supply passages in accordance with procedures outlined in Teledyne Continental Service Bulletin M74-21. After compliance with this bulletin, if it is determined that an oil passage has been omitted the engine must be removed from service. This amendment becomes effective October 28, 1974.