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2018-26-04: We are adopting a new airworthiness directive (AD) for certain Airbus SAS Model A350-941 and -1041 airplanes. This AD was prompted by a report that due to an issue with the flight warning system (FWS) logic, it is possible that the ``AIR Auxiliary Power Unit (APU) BLEED LEAK'' electronic centralized aircraft monitoring (ECAM) alert can trigger several times. This AD requires revising the airplane flight manual (AFM) to incorporate procedures related to an APU bleed leak. We are issuing this AD to address the unsafe condition on these products.
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98-17-10: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 98-17-10 that was sent previously to all known U.S. owners and operators of Pratt & Whitney Canada (PWC) PW530A series turbofan engines by individual letters. This AD requires recording engine surge events in the aircraft maintenance records. If an engine surge event is experienced, this AD requires, prior to the next flight, inspecting that engine for evidence of second stage stator vanes rubbing on the compressor rotor. In addition, this AD requires reworking all affected engines to increase the clearance between the second stage stator vanes and the compressor rotor. This amendment is prompted by reports of 4 inflight engine shutdowns and 2 additional unscheduled engine removals for significant compressor rotor damage. The actions specified by this AD are intended to prevent an inflight engine shutdown due to rubbing of the second stage stator vanes on the compressor rotor.
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80-08-06 R1: 80-08-06 R1 GENERAL ELECTRIC COMPANY: Amendment 39-3740 as amended by Amendment 39- 4005. Applies to CJ610-8A and -9 turbojet and CF700-2D and -2D-2 turbofan engines with turbine disks identified by serial numbers below.
To prevent low cycle fatigue failure of turbine disks suspected to have foreign material segregation, accomplish the following within the next 50 cycles.
Remove from service first stage turbine disks, P/N 5011T75P01, and second stage turbine disks P/N 5011T76P01, with serial numbers listed below and replace with serviceable disks:
SERIAL NUMBERS:
FIRST STAGE:
GATWZA 00585
GATWZA 00637
GATWZA 00677
GATWZA 00587
GATWZA 00640
GATWZA 00679
GATWZA 00599
GATWZA 00641
GATWZA 00680
GATWZA 00601
GATWZA 00642
GATWZA 00681
GATWZA 00604
GATWZA 00644
GATWZA 00682
GATWZA 00607
GATWZA 00645
GATWZA 00683
GATWZA 00610
GATWZA 00646
GATWZA 00687
GATWZA 00611
GATWZA 00647
GATWZA 00690
GATWZA 00613
GATWZA 00649
GATWZA 00691
GATWZA 00615
GATWZA 00652
GATWZA 00692
GATWZA 00616
GATWZA 00658
GATWZA 00693
GATWZA 00617
GATWZA 00662
GATWZA 00704
GATWZA 00618
GATWZA 00663
GATWZA 00705
GATWZA 00624
GATWZA 00664
GATWZA 00706
GATWZA 00626
GATWZA 00665
GATWZA 00707
GATWZA 00627
GATWZA 00667
GATWZA 00708
GATWZA 00630
GATWZA 00671
GATWZA 00709
GATWZA 00632
GATWZA 00672
GATWZA 00710
GATWZA 00633
GATWZA 00673
GATWZA 00713
GATWZA 00634
GATWZA 00674
GATWZA 00714
GATWZA 00635
GATWZA 00676
GATWZA 00715
FIRST STAGE:
OJAWZA 11J774-22
OJAWZA 11J796-20
OJAWZA 11J796-01
OJAWZA 11J796-21
OJAWZA 11J796-03
OJAWZA 11J796-23
OJAWZA 11J796-04
OJAWZA 11J796-24
OJAWZA 11J796-05
OJAWZA 11J796-31
OJAWZA 11J796-06
OJAWZA 11J796-32
OJAWZA 11J796-07
OJAWZA 11J796-35
OJAWZA 11J796-08
OJAWZA 11J796-41
OJAWZA 11J796-09
OJAWZA 11J796-42
OJAWZA 11J796-11
OJAWZA 11J796-43
OJAWZA 11J796-13
OJAWZA 11J796-44
OJAWZA 11J796-15
OJAWZA 11J796-45
OJAWZA 11J796-16
SECOND STAGE:
GATWZA 00541
GATWZA 00583
GATWZA 00614
GATWZA 00542
GATWZA 00585
GATWZA 00616
GATWZA 00545
GATWZA 00587
GATWZA 00617
GATWZA 00547
GATWZA 00588
GATWZA 00618
GATWZA 00548
GATWZA 00589
GATWZA 00619
GATWZA 00549
GATWZA 00590
GATWZA 00621
GATWZA 00550
GATWZA 00592
GATWZA 00622
GATWZA 00551
GATWZA 00593
GATWZA 00623
GATWZA 00552
GATWZA 00594
GATWZA 00624
GATWZA 00553
GATWZA 00595
GATWZA 00630
GATWZA 00554
GATWZA 00596
GATWZA 00632
GATWZA 00557
GATWZA 00597
GATWZA 00634
GATWZA 00563
GATWZA 00598
GATWZA 00636
GATWZA 00564
GATWZA 00600
GATWZA 00637
GATWZA 00565
GATWZA 00601
GATWZA 00638
GATWZA 00566
GATWZA 00602
GATWZA 00640
GATWZA 00567
GATWZA 00604
GATWZA 00642
GATWZA 00570
GATWZA 00605
GATWZA 00643
GATWZA 00571
GATWZA 00607
GATWZA 00646
GATWZA 00574
GATWZA 00609
GATWZA 00648
GATWZA00575
GATWZA 00610
GATWZA 00649
GATWZA 00577
GATWZA 00611
GATWZA 00651
GATWZA 00580
GATWZA 00612
GATWZA 00581
GATWZA 00613
SECOND STAGE:
OJAWZA 11J781-01
OJAWZA 11J781-19
OJAWZA 11J781-02
OJAWZA 11J781-20
OJAWZA 11J781-03
OJAWZA 11J781-21
OJAWZA 11J781-04
OJAWZA 11J781-22
OJAWZA 11J781-05
OJAWZA 11J781-23
OJAWZA 11J781-06
OJAWZA 11J781-24
OJAWZA 11J781-07
OJAWZA 11J781-25
OJAWZA 11J781-08
OJAWZA 11J781-26
OJAWZA 11J781-09
OJAWZA 11J781-27
OJAWZA 11J781-10
OJAWZA 11J781-28
OJAWZA 11J781-11
OJAWZA 11J781-29
OJAWZA 11J781-12
OJAWZA 11J781-31
OJAWZA 11J781-13
OJAWZA 11J781-32
OJAWZA 11J781-14
OJAWZA 11J781-33
OJAWZA 11J781-15
OJAWZA 11J781-34
OJAWZA 11J781-16
OJAWZA 11J781-35
OJAWZA 11J781-17
OJAWZA 11J781-37
OJAWZA 11J781-18
OJAWZA 11J781-38
General Electric Company Alert Service Bulletin Nos. (CJ610) A72-135, Addendum 1, dated May 19, 1980, and (CF700) A72-142, Addendum 1, dated May 19, 1980, refer to this subject.
This amendment was effective upon receipt of the Emergency Airworthiness Directive dated May 30, 1980, and is effective to all others on February 2, 1981.
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62-11-02: 62-11-02 GENERAL ELECTRIC: Amdt. 437 Part 507 Federal Register May 12, 1962. Applies to All Models CJ805-23, CJ805-23B, and CJ805-23C Turbofan Engines.
Compliance required as indicated.
To preclude low cycle fatigue failure of the fan bluckets, remove GE P/N's 109R164P1, 107R392P1, 107R362P5, 107R362P6, 109R200P1, or 109R197P1 from engines and retire from further service upon accumulation of operating cycle life limit as scheduled in GE Alert Service Bulletins Nos. A/23/72-58 and A/23B/72-18, unless the engine is operated in conjunction with an inspection program approved by FAA Eastern Region Engineering and Manufacturing Branch. Under an approved inspection program, the bluckets shall be removed from service and replaced with new units when inspection dictates. For the purposes of this AD, an operating cycle is considered to be an excursion of engine operation from engine start to takeoff to shutdown. Restart in the air is also a cycle. Ground operations encompassinga start and operation to takeoff power is a cycle.
This directive effective upon publication in the Federal Register for all persons except those to whom it was made effective immediately by telegram dated April 26, 1962.
This supersedes AD 62-09-03.
Revised September 7, 1962.
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2005-23-21: The FAA is adopting a new airworthiness directive (AD) for all Airbus Model A340-200 and A340-300 series airplanes. This AD requires repetitive inspections for cracking of the junction between the thrust reverser forward frame and the 12 o'clock and 6 o'clock beams; the thrust reverser common fittings; and the thrust reverser J-ring structure at the 12 o'clock and 6 o'clock positions; and related investigative and corrective actions. This AD results from fatigue and damage tolerance testing of the engine thrust reversers which revealed fatigue cracking of the junction between the thrust reverser forward frame and the 12 o'clock beam, and of the thrust reverser J-ring structure. We are issuing this AD to detect and correct such fatigue cracking, which could result in rupture of the J-ring, forward frame, or common fittings; loss of the thrust reverser system; or inadvertent deployment of a thrust reverser in flight and consequent reduced controllability of the airplane.
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98-21-11: This amendment adopts a new airworthiness directive (AD) that is applicable to certain Boeing Model 737-700 and -800 series airplanes. This action requires a one-time inspection to determine the serial numbers of the fire detector assemblies and elements for the auxiliary power unit (APU) and engines, and replacement of the assemblies or elements with new or serviceable parts, if necessary. This amendment is prompted by a report indicating that certain fire detector elements were not checked for leaks during manufacturing and, therefore, may not have the correct set points for the fire warning system. The actions specified in this AD are intended to prevent failure of the APU or engine fire detection systems to detect a fire in a timely manner, which could result in egress of an APU or engine compartment fire to other parts of the airplane.
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98-20-39: This amendment adopts a new airworthiness directive (AD) that applies to certain Mitsubishi Heavy Industries, Ltd. (Mitsubishi) MU-2B series airplanes. This AD requires inspecting each forward attachment fitting bolt of the wing tip tanks for the correct bolt and replacing any incorrect bolt. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Japan. The actions specified by this AD are intended to prevent the wing tip tank from separating from the airplane because of an incorrect bolt corroding, which could result in loss of control of the airplane.
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56-21-04: 56-21-04 RUSSELL: Applies to Safety Belts Equipped With Russell Manufacturing Co.'s 2 Inch Rusco Tog-L-Lok Safety Belt Buckle.
Compliance required as soon as possible but not later than December 30, 1956.
Recurring instances have been reported wherein Russell Model RM-3 and RM-4 belt assemblies have slipped and unlocked under relatively low tension loads. Accordingly, it has been determined that safety belt assemblies RM-3 and RM-4 manufactured between July 1, 1954, and August 1, 1956, as meeting Technical Standard Order C22b standards and equipped with Rusco Tog-L-Lok buckles, are unairworthy and must be reworked or replaced with belt assemblies that conform to TSO-C22b standards. Due to the need for precise jigs to accomplish the rework of these assemblies, reworking in the field is not feasible. However, the Russell Manufacturing Co. has submitted satisfactory substantiating data for reworking the unsatisfactory safety belt assemblies at the factory.
In addition to the above difficulty, some of the faulty Tog-L-Lok buckles may have been sold as, or on, military surplus equipment and, therefore, there is some likelihood that other companies or individuals may have renovated or manufactured and sold safety belt assemblies which incorporate these faulty buckles. The characteristics of these buckles are such that if the assembly does not slip or unlock under a maximum tensile load of 100 pounds, the belt assembly is satisfactory. Accordingly, a maximum tensile load of 100 pounds need be applied to these belt assemblies to check their airworthiness. If the assembly does not slip or unlock under this load, the assembly may be considered satisfactory and rework or replacement is not necessary.
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85-02-02: 85-02-02 AIRBUS INDUSTRIE: Amendment 39-4986. Applies to Model A300 B2 and B4 series airplanes, certificated in all categories. To detect failure of the ram air turbine, accomplish the following, unless previously accomplished:
A. Prior to the later of the following:
1. 3,400 hours total time in service;
2. 24 months since installed, either new or overhauled; or
3. 120 days after the effective date of this AD; perform a functional test of the ram air turbine in accordance with the accomplishment instructions of Dowty Rotol Service Bulletins 29-101 dated January 4, 1979, and 29-72 dated April 12, 1976. Repeat the functional test at intervals not to exceed 600 hours time in service or 6 months, whichever occurs first.
B. If, as a result of the functional test of paragraph A., above, it is found that the ram air turbine does not meet the specifications, the affected unit must be replaced with a serviceable unit before further flight.
C. Termination ofthe requirements of this AD is accomplished by incorporation of the following two Dowty Rotol modifications: RM 401, described in Service Bulletin 29-104 dated January 24, 1979, and RM 370, described in Service Bulletin 29-76 dated November 18, 1976.
D. Alternate means of compliance which provide an equivalent level of safety may be used when approved by the Manager, Seattle Aircraft Certification Office, 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 inspections and/or modifications required by this AD.
This amendment becomes effective March 1, 1985.
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60-26-05: 60-26-05 LOCKHEED: Amdt. 236 Part 507 Federal Register December 22, 1960. Applies to All 188 Series Aircraft.
Compliance required as indicated.
(a) Within the next 150 hours' time in service commencing on November 22, 1960, unless already accomplished within the last 300 hours' time in service, inspect the elevator counterweight installation, Lockheed Drawing No. 829912, at airplane center line for evidence of free play as follows: with elevator blocked at extreme down position apply up and down force to balance weight Lockheed P/N 827020-1, and measure total movement of balance weight due to cumulative free play in joints of balance arm linkage. If movement of balance weight due to cumulative free play in system exceeds 1/8-inch inspect each joint in balance arm linkage and reduce the free play by bolt and/or part replacement at one or more of these joints so as to reduce total free play movement of the balance weight to 1/16-inch or less prior to further flight. This inspection must be repeated every 450 hours' time in service. When provisions of paragraph (c)(1) are accomplished, this special inspection may be discontinued.
(b) Within the next 300 hours' time in service, unless already accomplished within the last 700 hours' time in service, and following any occurrence of inflight elevator or control column oscillations, inspect the elevator booster control valve viscous damper diaphragm, Lockheed P/N 813612-1 for evidence of rupture. See Lockheed Electra (Model 188) Overhaul Manual Section 27-1-10 Page 1 for information on evidence of rupture. If such evidence is found the airplane shall not be returned to service until the diaphragm is replaced with a new part, or compliance with paragraph (c)(2) has been accomplished. This inspection must be repeated at periods not to exceed 1,000 hours' time in service until the provisions of paragraph (c)(2) have been accomplished.
(c) The following must be accomplished within the next 1,000 hours' time in service.
(1) Install a spring-loaded cartridge, Lockheed P/N 840404-1, in the elevator counterweight linkage in the manner described by Lockheed Service Bulletin 88/SB-524.
(2) Replace the elevator boost control valve viscous damper, Lockheed P/N 813608-3, with an orifice type damper, Lockheed P/N 492508-3, in accordance with Lockheed Service Bulletin No. 88/SB-524.
(3) Rework the elevator booster assembly in accordance with Lockheed Service Bulletin No. 88/SB-524 to incorporate an orifice valve assembly, Lockheed P/N 804551-1, and modify the booster piston rod end installation to incorporate two retaining washers, Lockheed P/N 839756-1, in accordance with Lockheed Service Bulletin No. 88/SB-498.
(FAA approved Lockheed Service Bulletins 88/SB-498 and 88/SB-524, Lockheed Electra operating information letter No. 13 dated November 1, 1960, Lockheed Alert Bulletin No. 524 dated December 1, 1960, cover portions of this subject.)
This supersedes AD 60-24-02.
Thisdirective effective December 22, 1960.
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