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79-10-16: 79-10-16 BOEING: Amendment 39-3474. Applies to all Boeing 707-300/-400/-300B/-300C airplanes noted in Boeing Service Bulletin 3356: \n\tNo later than December 31, 1980, modify the horizontal stabilizer in accordance with the terminating action specified in Boeing Service Bulletin 3356, or in a manner approved by the Chief, Engineering and Manufacturing Branch, FAA Northwest Region. \n\tThe 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 the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington 98124. These documents may also be examined at FAA, Northwest Region, 9010 East Marginal Way South, Seattle, Washington 98108. \n\n\tThis amendment becomes effective June 25, 1979.
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2009-12-09: 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:
* * * * *
[C]hafed wirings were found in the rear baggage zone, closed [close] to the forward side of the aft pressure bulkhead, due to contact with an understructure securing screw. The concerned wiring harness includes rudder trim, pitch trim and stick pusher control wires. Damages on those wires might lead to the loss of fail safe criteria for those critical functions.
* * * * *
The unsafe condition is reduced controllability of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.
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80-25-02 R2: 80-25-02 R2 AVCO LYCOMING: Amendment 39-4016. Applies to O-235 series engines with Serial Numbers L-12500-15 thru L-20676-15 inclusive, all remanufactured O-235 series engines, regardless of serial number, shipped between December 10, 1976, and November 8, 1979, and all O-235 series engines regardless of serial number that had pushrods replaced between December 10, 1976, and November 24, 1980.
Model O-235 series engines are installed in but not limited to, Piper PA-38-112, Cessna 152, Gulfstream American AA1C, Beech 77, and Bellanca 7ECA aircraft.
This AD does not apply to O-235 series engines incorporating eight pushrods P/N 73806, identified by revision letter K or subsequent revision letter, or by code T-T, -85 or the symbol # as described in Lycoming Service Bulletin No. 453 or a subsequent approved revision.
Compliance with this AD is also required by the following engine serial numbers which were previously exempt by Emergency Airworthiness Directive 80-25-02 R1:L-15619-15
L-19029-15
L-20155-15
L-20385-15
L-16333-15
L-19030-15
L-20156-15
L-20386-15
L-17291-15
L-19031-15
L-20157-15
L-20387-15
L-17644-15
L-19145-15
L-20158-15
L-20388-15
L-18054-15
L-19146-15
L-20172-15
L-20389-15
L-18055-15
L-19147-15
L-20173-15
L-20428-15
L-18073-15
L-19148-15
L-20174-15
L-20429-15
L-18074-15
L-19149-15
L-20175-15
L-20430-15
L-18141-15
L-19766-15
L-20176-15
L-20431-15
L-18142-15
L-19767-15
L-20242-15
L-20432-15
L-18207-15
L-19768-15
L-20243-15
L-20460-15
L-18208-15
L-19990-15
L-20244-15
L-20461-15
L-18502-15
L-19991-15
L-20245-15
L-20462-15
L-18503-15
L-19992-15
L-20246-15
L-20463-15
L-18601-15
L-19993-15
L-20323-15
L-20464-15
L-18948-15
L-19994-15
L-20324-15
L-20523-15
L-18949-15
L-19995-15
L-20325-15
L-20524-15
L-18950-15
L-19996-15
L-20326-15
L-20525-15
L-18951-15
L-19997-15
L-20327-15
L-20526-15
L-19028-15
L-19999-15
L-20384-15
L-20527-15
L-20609-15
L-20610-15
L-20611-15
L-20612-15
Compliance required as indicated:
In order to prevent failures of engine pushrods which can cause rough engine operation and power loss, accomplish the following:
1. Prior to further flight, remove all eight pushrods and inspect for loose ball ends and evidence of bulging and splitting of the pushrod tubing. Measure the length of the pushrod assembly. The overall length shall not be less than 11 17/32 inches. If all these conditions are satisfactory set valve clearances in accordance with Paragraph 8 of Lycoming Service Instructions Nos. 1388A dated January 25, 1980, and 1068A dated September 1, 1978. If any pushrod is found damaged or is less than the specified dimension noted above, replace with a serviceable part prior to further flight.
2. Within 25 hours in service after the effective date of this AD and every 25 hours thereafter, measure and record valve tappet clearances inaccordance with Lycoming Service Instructions 1388A and 1068A. If any valve clearance increases more than .015 inch since the last 25 hour inspection, remove the pushrod and inspect for damage and shortening in accordance with Item 1 above.
3. The 25 hour repetitive inspection described in Paragraph 2 above may be discontinued upon installation of P/N 73806 pushrods which have been identified by one of the codes specified in this AD.
4. A special flight permit may be issued in accordance with FAR 21.197 to fly the aircraft to a base where the above inspections may be accomplished.
5. Equivalent methods of compliance must be approved by the Chief, Engineering and Manufacturing Branch, FAA Eastern Region.
(Beech Aircraft Corp. Executive Airplane Service Communique No. 52 dated December 16, 1980, pertains to this subject.)
This Amendment becomes effective Jan. 13, 1981, to all persons except those to whom it was made effective by airmail letters dated November 25, 1980, November 28, 1980, and December 3, 1980.
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82-03-06: 82-03-06 MCDONNELL DOUGLAS: Amendment 39-4311. Applies to McDonnell Douglas Model DC-9-10, -20, -30, -40, -50, and -80 series airplanes, including C-9A, C-9B, and VC-9C airplanes, certificated in all categories, equipped with Kevlar tailcones. Compliance required within the next 900 hours time-in-service from the effective date of this AD, unless already accomplished. To assure proper operation of the tailcone emergency exit release mechanism on aircraft utilizing tailcone assemblies P/N 5910233-505 or P/N 5910233-507, accomplish the following: \n\n\tA.\tReplace or modify the tailcone lock housing as outlined in the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 53-158 dated July 15, 1981, or later revisions approved by the Chief, Los Angeles Area Aircraft Certification Office, Northwest Mountain Region. \n\n\tB.\tAlternate means of compliance with the AD which provide an equivalent level of safety may be used when approved by the Chief, Los Angeles Area Aircraft Certification Office, Northwest Mountain Region. \n\n\tSpecial 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. \n\n\tThis Amendment becomes effective March 11, 1982.
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63-08-05: 63-08-05 SUD AVIATION: Amdt. 557 Part 507 Federal Register April 18, 1963. Applies to All SE-210 Caravelle Mark III and VIR Aircraft.
Compliance required within 300 hours' time in service after the effective date of this AD on aircraft with 2,700 or more hours' time in service on the effective date of this AD or before 3,000 hours' time in service on aircraft with less than 2,700 hours' time in service on the effective date of this AD.
To prevent overtorquing and possible failure of frequently removed flight control system bolts and to prevent failure of flight controls, accomplish the following:
(a) Remove the flight control system bolts having a shank diameter less than 6 mm. and replace them with new bolts in accordance with Sud Service Bulletin No. 27-131, Revision 2, dated October 4, 1962.
(b) Modify flight control rod ends and bellcranks in accordance with Sud Caravelle Service Bulletin No. 27-138, Revision 1, dated July 3, 1962.
NOTE: Provision (b) makes it physically impossible for improper installation of these units. Bulletin No. 27-138 lists parts which must be added on specified aircraft.
This directive effective May 20, 1963.
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2009-11-09: 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:
An A300-600 operator reported a recent event which occurred during the take-off roll, where a SOGERMA co-pilot seat slid back uncommanded to the end position. The seat horizontal movement actuator was replaced on the affected co-pilot seat. At the following take-off roll the same event occurred, the co-pilot seat sliding back uncommanded again. * * *
An unwanted movement of pilot or co-pilot seat in the horizontal direction is considered as potentially unsafe, especially during the take-off phase when the speed of the aeroplane is greater than 100 knots and until landing gear retraction.
* * * * *
Uncommanded movement of the pilot and co-pilot seats during takeoff or landing could interfere with the operation of the airplane and, as a result, could cause consequent loss of control of the airplane. This AD requires actions that are intended to address the unsafe condition described in the MCAI.
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80-12-15: 80-12-15 ROSEMOUNT, INC.: Amendment 39-3848. Applies to all Model 856 AE-12, -13, and -15 Pitot-Static Probes up to and including S/N 49529.
Compliance is required as indicated unless already accomplished. To prevent icing of the Pitot-Static Probe, accomplish the following:
Within the next 100 hours time in service, conduct resistance checks of the Pitot-Static Probe heater element in accordance with procedures in paragraph 10, Parts II and III of Boeing Alert Service Bulletin 737-30A1018 dated June 9, 1980 or FAA approved equivalent. All probes, including spares, serial numbers up to and including S/N 49529, must be checked. Probes with resistance values less than the minimum limits in the Boeing Alert Service Bulletin are considered defective. Dispatch of an airplane with defective probe heaters is limited to the minimum equipment list (MEL) restriction for operation with a failed Pitot-Static Probe heater (MEL Item 30-5). A defective probe falls into the categoryof an inoperative probe heater for MEL dispatch purposes. Upon request of the operator an equivalent means of compliance with the requirements of this AD may be approved by the Chief, Engineering and Manufacturing Branch, FAA, Great Lakes Region.
This amendment becomes effective July 25, 1980, as to all persons except those to whom it was made immediately effective by airmail letter dated June 11, 1980, which contained this amendment.
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2009-10-12: The FAA is superseding an existing airworthiness directive (AD) that applies to certain Boeing Model 747 airplanes. The existing AD currently requires modifying the inflation systems of the upper deck escape slides; single-piece off-wing escape ramps/slides; two-piece off-wing escape slides; and door 1, 2, 4, and 5 escape slides/rafts; as applicable. This AD expands the applicability to include an additional airplane. This AD results from a report of 30- to 60-second delays in the inflation of escape slides/rafts. We are issuing this AD to prevent actuation delays in the inflation systems of the escape slides/rafts, which could result in delayed or failed deployment of escape slides/ rafts during emergency evacuation of an airplane.
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81-08-03: 81-08-03 GOVERNMENT AIRCRAFT FACTORIES (GAF): Amendment 39-4084. Applies to Nomad Model N22B (Serial Nos. N22B-5 and up) and Model N24A (Serial Nos. N24A-42 and up), airplanes certificated in all categories.
Compliance required as indicated, unless already accomplished.
To reduce the rate of wear experienced in the horizontal stabilizer trim tab control linkages and prevent instability due to excessive free play, accomplish the following:
(a) Within the next 50 hours time in service after the effective date of this AD, unless already accomplished, modify the horizontal stabilizer structure to accept the balanced trim tabs in accordance with Part A, "ACCOMPLISHMENT INSTRUCTIONS," of GAF Nomad Service Bulletin NMD-55-12, dated August 29, 1980, (hereinafter referred to as the Service Bulletin), or an FAA-approved equivalent. The trim tabs previously modified in accordance with Service Bulletin NMD-55-8 may be reinstalled until paragraph (b) is accomplished.
(b) Within the next 100 hours time in service after the effective date of this AD, unless already accomplished, install the balanced trim tabs in accordance with Part B of the Service Bulletin, or an FAA-approved equivalent.
(c) If an equivalent means of compliance is used in complying with paragraphs (a) and (b) of this AD, that equivalent means must be approved by the Chief, Engineering and Manufacturing District Office, FAA, Pacific-Asia Region, Honolulu, Hawaii.
This amendment becomes effective April 23, 1981.
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80-04-01: 80-04-01 MITSUBISHI: Amendment 39-3686. Applies to: Model MU-2B-36 aircraft serial numbers 675, 681, 684, 687, 688, 691, and 695; models MU-2B-36A, and MU-2B-60, serial numbers 697SA, 699SA, 701SA, 706SA, 708SA, 709SA, 711SA, 713SA, 714SA, 719SA, 720SA, 721SA, 723SA, 725SA, 727SA, 729SA through 736SA, 738SA through 747SA, 749SA through 757SA, 759SA, 761SA, 763SA and 765SA.
Compliance is required within the next 25 hours of flight time, after the effective date of this AD, unless already accomplished.
To assure a reliable attitude reference and retain eligibility for IFR operation, install an improved avionic equipment mounting shelf in accordance with: (1) Mitsubishi Aircraft International Service Note No. 062 dated November 30, 1979, on affected Serial Number MU- 2B-36 aircraft, or (2) Mitsubishi Aircraft International Service Bulletin SB015/53-001 dated November 30, 1979, on affected serial number MU-2B-36A and MU-2B-60 aircraft.
If the improved avionic equipment mounting shelf is not installed within the 25 hour compliance period, aircraft operations are limited to day VFR only. In this event install a placard stating "OPERATIONS LIMITED TO DAY VFR" with letters a minimum of 1/4 inch high in clear view on the pilot's instrument panel. The placard and limitation can be removed upon incorporation of the improved avionic equipment shelf.
The manufacturer's instructions 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 of the Service Bulletin or Service Note upon request to Mary Ann Lowry, Publications Group, Mitsubishi Aircraft International, P.O. Box 3848, San Angelo, Texas 76901; telephone (915) 944-1511, extension 269; Telex 73-9438.
These documents may also be examined at the Office of the Regional Counsel, Southwest Region, FAA, 4400 Blue Mound Road, Fort Worth, Texas, and at FAA Headquarters, 800 Independence Avenue, S.W., Washington, D.C. A historical file on this AD which includes the incorporated material in full is maintained by the FAA at its headquarters in Washington, D.C., and at the Southwest Regional Office in Fort Worth, Texas.
This amendment becomes effective February 14, 1980.
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