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77-14-02: 77-14-02 SOCIETE NATIONALE INDUSTRIELLE AEROSPATIALE: Amendment 39- 2950. Applies to Puma Model SA 330F and SA 330G helicopters that have not been modified in accordance with Puma Service Bulletin No. 53.13.
Compliance is required within the next 50 hours time in service after the effective date of this AD and thereafter at intervals not to exceed 50 hours time in service since the last inspection, until accomplishment of Puma Service Bulletin No. 53.13, dated May 29, 1974, or an FAA- approved equivalent.
To prevent possible failure of the forward engine mount support structure, accomplish the following:
(a) Inspect for cracks in beams under attachment fittings for the forward engine mounts located between frames 3245 and 3550 in accordance with subparagraph 1C(1) of Puma Service Bulletin No. 05.35, dated April 9, 1974, or an FAA-approved equivalent.
(b) If cracks are found which exceed the criteria for continued service set forth in subparagraph 1C(2) of PumaService Bulletin No. 05.35, before further flight, except that the helicopter may be flown in accordance with FAR Sections 21.197 and 21.199, to a base where the work can be performed, replace the beams in accordance with Puma Service Bulletin No. 53.13, dated May 29, 1974, or an equivalent approved by the Chief, Aircraft Certification Staff, FAA, Europe, Africa, and Middle East Region, c/o American Embassy, APO, New York, N.Y. 09667.
This amendment becomes effective August 1, 1977.
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2013-20-16: We are adopting a new airworthiness directive (AD) for MDHI Model MD900 helicopters with certain main rotor blade (MRB) retention bolts (bolts) installed. This AD requires a daily check of the position of each bolt, a daily check and a repetitive inspection for a gap in each bolt, and, if necessary, removing and inspecting the bolt for a crack and replacing any cracked bolt with an airworthy bolt. This AD was prompted by multiple reports of in-service bolt failures. The actions are intended to prevent failure of a bolt, which could lead to loss of MRB structural integrity and subsequent loss of control of the helicopter.
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2013-20-15: We are superseding Airworthiness Directive (AD) 97-19-10 for Sikorsky Aircraft Corporation-manufactured Model S-64E helicopters (type certificate currently held by Erickson Air-Crane Incorporated (Erickson)). AD 97-19-10 required inspecting and reworking the main gearbox (MGB) assembly second stage lower planetary plate (plate). This action establishes or reduces the life limits for certain flight- critical components, removes from service various parts, requires repetitive inspections and other corrective actions, and requires replacing any cracked part discovered during an inspection. This AD is prompted by further analysis performed by the current type certificate holder and the service history of certain parts. The actions specified in this AD are intended to prevent a crack in a flight critical component, failure of a critical part, and subsequent loss of control of the helicopter.
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2013-20-10: We are superseding airworthiness directive (AD) 2000-12-11, for certain Model A300 B4-600 and Model A300 B4-600R series airplanes. AD 2000-12-11 required repetitive inspections to detect cracks in the bolt holes inboard and outboard of rib 9 on the bottom booms of the front and rear wing spars, and repair if necessary. This new AD reduces the initial inspection compliance time and repetitive inspection interval. This AD was prompted by a fleet survey and an updated fatigue and damage tolerance analysis indicating a high risk for fatigue cracking on the front and rear spar bottom booms. We are issuing this AD to detect and correct fatigue cracks in the bolt holes of the wing spars, which could result in reduced structural integrity of a wing spar.
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76-07-13: 76-07-13 HAMBURGER FLUGZEUGBAU GmbH: Amendment 39-2579. Applies to Model HFB-320 airplanes, S/N 1021 thru 1023, 1026 thru 1028, 1030 thru 1040, 1045, and 1049 thru 1057, certificated in all categories.
Compliance is required within the next 25 hours time in service after the effective date of this AD, unless already accomplished.
To detect possible incorrect adjustment of camlocks that could result in cracking of the camlock housing, possible inadvertent opening of the door, and inflight explosive decompression, accomplish the following:
(a) Inspect the camlocks for correct adjustment in accordance with the accomplishment instructions contained in Section B, Part 1, of HFB Hansa Alert Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976, or an FAA-approved equivalent.
(b) If a camlock is found out of adjustment beyond the tolerances specified in HFB Hansa Alert Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976,or an FAA-approved equivalent, rectify the camlock adjustment in accordance with the accomplishment instructions contained in Section B, Part 2, of Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976, or an FAA-approved equivalent.
(c) Inspect the door frame camlock housings, which house the camlocks for which adjustment is required in accordance with paragraph (b) of this AD, for cracks, using a dye penetrant method in accordance with the instructions contained in Section B, Part 3, of HFB Hansa Alert Service Bulletin 53-21A, dated October 13, 1975, as revised January 20, 1976, or an FAA-approved equivalent.
(d) If any cracks are found in the door frame camlock housing during the inspection required by paragraph (c) of this AD, before further flight, except that the aircraft may be flown unpressurized in accordance with FAR's 21.197 and 21.199 to a base where the replacement can be accomplished, replace the camlock housing with a new part of the samepart number.
This amendment becomes effective, April 26, 1976.
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2013-22-07: We are adopting a new airworthiness directive (AD) for certain The Boeing Company Model 747-400 series airplanes. This AD was prompted by reports of fasteners missing on an airplane undergoing a passenger- to-freighter conversion. This AD requires doing a general visual inspection of the station 1920 splice clip for correct fastener installation, and related investigative and corrective actions if necessary. We are issuing this AD to detect and correct missing or incorrect fasteners, which can lead to cracking and loss of load carrying capacity, resulting in a possible decompression event.
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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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