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90-21-03: 90-21-03 BELL HELICOPTER TEXTRON, INC. (BHTI): Amendment 39-7072. Docket No. 90-ASW-44. Final Rule of Priority Letter AD 90-21-03.
Applicability: All BHTI Model 206A, 206A-1, 206B, 206B-1, 206L, 206L-1 and 206L-3 helicopters, certificated in any category, with tail rotor blade assembly, P/N 206-016-201-125 or - 127.
Compliance: Required before further flight, unless already accomplished.
To prevent the loss of a tip weight, failure of the tail rotor blade assembly, loss of the tail rotor hub assembly and subsequent loss of control of the helicopter, accomplish the following:
(a) Before further flight, inspect the aircraft to determine the part number and serial number of the installed tail rotor blade assembly. If P/N 206-016-201-125 or -127 with a serial number listed below is installed on the helicopter, remove and replace the assembly with an airworthy blade assembly.
For 206-016-201-127 T/R BLADE
CS-0203
CS-0206
CS-0238
CS-0985
CS-1141
CS-1153
CS- 1207
CS-1210
CS-1219
CS-1229
CS-1232
CS-1235
CS-1252
CS- 1304
CS-1306
CS-1316
CS-1325
CS-1332
CS-1337
CS-1342
CS- 1351
CS-1354
CS-1359
CS-1360
CS-1368
CS-1373
CS-1375
CS- 1380
CS-1391
CS-1461
CS-1466
CS-1476
CS-1489
CS-1519
CS- 1523
CS-1524
CS-1525
CS-1528
CS-1533
CS-1544
CS-1553
CS- 1555
CS-1556
CS-1557
CS-1559
CS-1563
CS-1564
CS-1566
CS- 1577
CS-1579
CS-1580
CS-1584
CS-1585
CS-1588
CS-1594
CS- 1597
CS-1599
CS-1612
CS-1614
CS-1635
CS-1642
CS-1647
CS-1656
CS-1670
CS-1673
CS-1685
CS-1705
CS-1716
CS-1726
CS- 1733
CS-1734
CS-1737
CS-1740
CS-1744
CS-1745
CS-1754
CS- 1756
CS-1760
CS-1771
CS-1778
CS-1784
CS-1827
CS-1830
CS- 1842
CS-1844
CS-1855
CS-1856
CS-1881
CS-1890
CS-1893
CS- 1894
CS-1900
CS-1901
CS-1907
CS-1909
CS-1913
CS-1914
CS- 1940
CS-1944
CS-1953
CS-1957
CS-1958
CS-1958
CS-1959
CS- 1961
CS-1978
CS-1979
CS-1981
CS-1982
CS-1983
CS-1985
CS- 1986CS-1989
CS-1994
CS-1997
CS-1998
CS-2000
CS-2003
CS- 2007
CS-2016
CS-2019
CS-2027
CS-2033
CS-2037
CS-2088
T-47310
T-47361
T-47371
T-47378
T-47397
T-47398
T- 47401
T-47426
T-47458
For 206-016-201-125 T/R BLADE
CS-136
CS-158
CS-398
CS-534
CS-625
CS-658
CS- 684
CS-685
CS-688
CS-690
CS-711
CS-715
CS-716
CS- 719
CS-720
CS-738
CS-740
CS-752
CS-807
CS-832
CS- 865
CS-871
CS-874
T-61995
(b) An alternate method of compliance which provides an equivalent level of safety, may be used if approved by the Manager, Rotorcraft Certification Office, Southwest Region, Federal Aviation Administration, Fort Worth, Texas 76193-0170, telephone (817) 624-5170.
This amendment (39-7072, AD 90-21-03) becomes effective on August 14, 1991, as to all persons except those persons to whom it was made immediately effective by Priority Letter AD 90-21-03 issued October 5, 1990, which contained this amendment.
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91-26-02: 91-26-02 BOEING OF CANADA, LTD., DE HAVILLAND DIVISION: Amendment 39- 8113. Docket No. 91-NM-183-AD.
Applicability: Model DHC-8-102 and -103 series airplanes, serial numbers 3 through 287, certificated in any category.
Compliance: Required as indicated, unless previously accomplished.
To prevent reduced engine-out takeoff and climb performance of the airplane, accomplish the following:
(a) Within 7 days after the effective date of this AD, remove Supplement No. 21, dated May 30, 1990 (for Model DHC-8-102 series airplanes), or September 26, 1990 (for Model DHC-8-103 series airplanes), from the de Havilland Airplane Flight Manual PSM 1-81-1A.
(b) Within 7 days after the effective date of this AD, revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM) by inserting the following statement. This may be accomplished by inserting a copy of this AD into the AFM.
"Supplement No. 21, dated May 30, 1990 (for Model DHC-8-102 series airplanes), or September 26, 1990 (for Model DHC-8-103 series airplanes), of the de Havilland Airplane Flight Manual PSM 1-81-1A, is withdrawn. Use of engine bleed air during takeoffs and landings is prohibited."
(c) An alternative method of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Transport Airplane Directorate.
NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Standardization Branch, ANM-113.
(d) Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base in order to comply with the requirements of this AD.
(e) This amendment (39-8113, AD 91-26-02) becomes effective on December 23, 1991.
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2013-21-02: We are superseding airworthiness directive (AD) 2012-24-09 for Lycoming Engines TIO-540-AK1A, and Continental Motors, Inc. (CMI) TSIO- 360-MB, TSIO-360-SB, and TSIO-360-RB reciprocating engines, with certain Hartzell Engine Technologies (HET) turbochargers, model TA0411, installed. AD 2012-24-09 required removing certain HET turbochargers from service before further flight. This AD also requires removing certain HET turbochargers from service before further flight. This AD was prompted by a report that an additional engine, the CMI LTSIO-360- RB, has the affected HET turbochargers installed. We are issuing this AD to prevent turbocharger turbine wheel failure, reduction or complete loss of engine power, loss of engine oil, oil fire, and damage to the airplane.
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51-11-01: 51-11-01 MARTIN: Applies to All Models 202 and 202A Airplanes Except as Noted.
Compliance required as specified herein.
Compliance with this note cancels the requirements of AD 50-41-02.
In order to comply with the recommendations of the Martin 202 Modification Board, the following items must be accomplished. In all cases, modifications which are demonstrated to provide a level of safety equivalent to that provided by the modifications listed herein will be acceptable in lieu of the listed modifications.
Compliance required by August 16, 1951.
1. Decrease breaker rating for propeller anti-icing circuit to 5 amperes to accommodate No. 20 wire. (Applies to Model 202 airplanes only.)
2. Install negative pressure scoop on battery vent line.
Compliance require by November 16, 1951.
1. Add manually operated charging valve in the emergency brake hydraulic system in accordance with Glenn L. Martin Co. Service Bulletin No. 185.
Compliance required by December 1, 1951.
1. Provide circuit protection for voltmeter.
2. Provide circuit protection at main bus for generator tip light circuit.
3. Provide circuit protection for ammeter wires.
Compliance required by February 1, 1952.
1. Install circuit breaker in circuit breaker panel with wire routed back to auxiliary bus control relay.
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2013-20-09: We are adopting a new airworthiness directive (AD) for certain Bombardier, Inc. Model CL-215-6B11 (CL-415 Variant) airplanes. This AD requires replacing the panel assembly of the main distribution center (MDC) rack. This AD was prompted by findings of chafed power wires due to flexing of the MDC rack panel. We are issuing this AD to prevent damage to power wires, which could cause simultaneous loss of systems such as electrical power, pilot indications, and caution/advisory lighting systems, which are essential for safe flight.
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2013-03-11: We are adopting a new airworthiness directive (AD) for certain Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-605R Variant F airplanes (collectively called A300-600 series airplanes); and Model A310 series airplanes. This AD was prompted by reports of cracking through the honeycomb core closed with phenolic resin. This condition could result in extended debonding and could adversely affect the structural integrity of the rudder. This AD requires inspecting to determine the serial number of a certain rudder and replacing the rudder with a new or serviceable rudder if necessary. We are issuing this AD to prevent extended de-bonding, which could result in loss of the rudder and consequent reduced controllability of the airplane.
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77-21-06: 77-21-06 PIPER: Amendment 39-3058. Applies to Models PA-25, PA-25-235 and PA-25-260, Serial Nos. 25-1 and up, certificated in all categories.
To prevent weakening of the fuselage steel tubing cluster in the area of the rear wing spar attachment due to corrosion of the fuselage tubing, accomplish the following:
(a) Within the next 30 days in service after the effective date of this AD or upon the attainment of a total of 1 year in service, whichever occurs later, unless previously accomplished within the last year and at intervals not to exceed 1 year from the last inspection, inspect the fuselage steel tubing cluster in the area of the rear wing spar attachment and repair if necessary, in accordance with the "Instructions" section of Piper Service Bulletin No. 551 dated April 22, 1977, or equivalent. The aircraft may be flown in accordance with FAR 21.197 to a base where inspection and repair can be made.
(b) Equivalent inspections and repairs must be approved bythe Chief, Engineering and Manufacturing Branch, FAA, Eastern Region.
(c) Upon submission of substantiating data by an owner or operator through an FAA Maintenance Inspector, the Chief, Engineering and Manufacturing Branch, FAA, Eastern Region may adjust the inspection intervals specified in this AD.
This amendment is effective October 19, 1977.
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2013-19-13: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-300, 747-400, 747-400D, and 747SP series airplanes. This AD was prompted by reports of worn or incorrectly assembled latches on main deck escape slides installed on airplane doors. This AD requires determining if the latches are correctly assembled; and doing corrective actions if necessary. This AD also requires, for certain airplanes, modifications to the escape slide/rafts and escape slides. We are issuing this AD to prevent a latch hook moving from closed to open in an escape slide/raft or escape slide, which could result in the escape slide/raft or escape slide not deploying correctly in an emergency, or releasing/inflating into the passenger cabin and causing injury to passengers and crew.
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91-24-03: 91-24-03 PRATT & WHITNEY CANADA: Amendment 39-8088. Docket No. 91-ANE-36. Supersedes AD 90-24-05, Amendment 39-6812.
Applicability: Pratt & Whitney Canada (PWC) PW123, PW124B, PW125B, and PW126A turboprop engines installed on but not limited to DeHavilland Dash 8 Series 300, Aerospatiale ATR72, Fokker 50, and British Aerospace ATP aircraft.
Compliance: Required as indicated, unless accomplished previously.
To prevent a low pressure turbine (LPT) overspeed, that could result in uncontained disk failure, and subsequent damage to the aircraft, accomplish the following:
(a) For PW123 and PW124B engines that have not been modified in accordance with any revision level of PWC Service Bulletin (SB) 21018, prior to the effective date of this AD, accomplish the following:
(1) Within 5 days after the effective date of this AD, perform a turbomachinery magnetic chip detector (MCD) continuity check in accordance with PWC SB 20938, Revision 2, dated November 18, 1991.
(2) Within 5 days after the effective date of this AD, perform a turbomachinery MCD functional check in accordance with PWC SB 20938, Revision 2, dated November 18, 1991.
(3) Thereafter, at intervals not to exceed 25 flight hours since last inspection, perform the turbomachinery MCD continuity check specified in paragraph (a)(1) of this AD.
(4) Thereafter, at intervals not to exceed 300 flight hours since last inspection, perform the turbomachinery MCD functional check specified in paragraph (a)(2) of this AD.
(b) In addition to the requirements of paragraph (a) of this AD, for PW123 engines that have not been modified in accordance with any revision level of PWC SB 21018, prior to the effective date of this AD, accomplish the following:
(1) Within 5 days after the effective date of this AD, perform a turbomachinery MCD airframe circuitry check in accordance with PWC SB 20938, Revision 2, dated November 18, 1991.
(2) Thereafter, at intervals not to exceed 300 flight hourssince last inspection, perform the turbomachinery MCD airframe circuitry check specified in paragraph (b)(1) of this AD.
(c) For PW125B and PW126A engines that have not been modified in accordance with any revision level of PWC SB 21018, prior to the effective date of this AD, accomplish the following:
(1) Within the next 125 flight hours after the effective date of this AD, unless previously accomplished within the last 875 flight hours, perform a turbomachinery MCD operational check in accordance with the applicable engine maintenance manual.
NOTE: Further information on the turbomachinery MCD operational check specified in paragraph (c)(1) can be found in PWC Maintenance Manual Part Number 3034932 for the PW125B, and PWC Maintenance Manual Part Number 3034922 for the PW126A.
(2) Within the next 125 flight hours after the effective date of this AD, unless previously accomplished within the last 875 flight hours, perform an operational check of the turbomachinery MCD airframe circuitry and indicating system in accordance with the applicable aircraft maintenance manual.
NOTE: Further information on the turbomachinery MCD airframe circuitry and indicating system specified in paragraph (c)(2) of this AD can be found in Fokker 50 Maintenance Manual, Chapter 77-33-00, for the PW125B, and BAe ATP Aircraft Maintenance Manual, Chapter 79-33-00, for the PW126A.
(3) Thereafter, at intervals not to exceed 1,000 flight hours since last inspection, perform the turbomachinery MCD operational check specified in paragraph (c)(1) of this AD.
(4) Thereafter, at intervals not to exceed 1,000 flight hours since last inspection, perform the operational check of the turbomachinery MCD airframe circuitry and indicating system in paragraph (c)(2) of this AD.
(d) The initial inspections of paragraphs (a)(1), (a)(2), and (b)(1) of this AD need not be accomplished for those PW123 and PW124B engines previously inspected in accordance with AD 90-24-05.
(e) Forengines that have not been modified in accordance with any revision level of PWC SB 21018, prior to the effective date of this AD, incorporate a new low pressure rotor balancing assembly in accordance with PWC SB 21018, Revision 2, dated November 25, 1991, at the next engine shop visit or by June 30, 1994, whichever occurs first. The incorporation of a new low pressure rotor balancing assembly in accordance with this paragraph constitutes a terminating action for paragraphs (a), (b), or (c), as applicable, of this AD.
(f) For the purpose of this AD, an engine shop visit is defined as the induction of an engine into a maintenance facility for the conduct of any type of maintenance.
(g) 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, Engine Certification Office, ANE-140, Engine and Propeller Directorate, Aircraft Certification Service, FAA, New England Region, 12 New England Executive Park, Burlington, Massachusetts. The request shall be forwarded through an FAA Principal Maintenance Inspector, who may concur or comment and then send it to the Manager, Engine Certification Office.
(h) 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.
(i) The inspections and modifications shall be done in accordance with the following Pratt & Whitney Canada service documents:
Document Number
Page Number
Issue/Rev
Date
PWC SB 21018R2
1-36
Revision 2
11/25/91
Total: 36 pages
PWC SB 20938R2
1-8
Revision 2
11/18/91
Total: 8 pages
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 Pratt & Whitney Canada, Technical Publications Department, 1000 Marie Victorin, Longueuil, Quebec J4G 1A1. Copiesmay be inspected at the FAA, New England Region, Office of the Assistant Chief Counsel, 12 New England Executive Park, Room 311, Burlington, Massachusetts, or at the Office of the Federal Register, 1100 L Street NW., Room 8401, Washington, D.C.
(j) This amendment becomes effective on May 26, 1992.
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78-03-01: 78-03-01\tBELL 47 SERIES AS MODIFIED BY STC SH357SW: Amendment 39- 3131. To preclude failure of the hopper upper support bracket, accomplish the following: \n\n\tWithin the next 25 hours flight time and at each 25 flight hours thereafter, inspect the hopper upper support bracket (P/N B630224) for cracks and/or deformation. If cracks and/or deformation are found, replace or repair. Inspections may be discontinued upon installation of Simplex Modification No. E201 (See Fig. 1), or equivalent modification or repair approved by an FAA Maintenance Inspector. \n\n\tThe manufacturer's repair, identified and described in this directive is incorporated herein and made a part hereof pursuant to 5 U.S.C. 552(a)(1). \n\n\tAll persons affected by this directive who have not already received the repair documents from the manufacturer, may obtain copies upon request to Simplex Manufacturing Company, 5224 N.E. 42nd Avenue, Portland, Oregon 97218. This repair document may also be examined at FAA Northwest Region, 9010 E. Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective March 6, 1978.
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