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83-16-03: 83-16-03 AVCO LYCOMING: Amendment 39-4676. Applies to Avco Lycoming Model LTS101-600A-2 engines, all Serial Numbers prior to but not including LE 43559.
Compliance is required as indicated unless already accomplished.
To prevent possible engine failure due to overspeed, accomplish the following:
Install Overspeed Limiter, P/N 4-301-235-04, per instructions provided in Avco Lycoming Service Bulletin No. LTS101A-73-0043, dated March 21, 1983, or equivalent method approved by the Manager, Engine Certification Branch, ANE-140, 12 New England Executive Park, Burlington, Massachusetts 01803.
Compliance required as follows:
A. Prior to 1,200 hours total time in service for engines with 1,000 or less hours total time in service on the effective date of this airworthiness directive, or
B. Within the next 200 hours time in service for engines with more than 1,000 hours total time in service on the effective date of this airworthiness directive, or
C. Before August 1, 1984,regardless of engine total time in service.
NOTE: Refer to the pertinent operations and maintenance manuals for operational check procedures and requirements.
Avco Lycoming Service Bulletin No. LTS101A-73-0043, dated March 21, 1983, identified and described in this directive is 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 this document from the manufacturer may obtain copies upon request to Avco Lycoming, Williamsport Division, Williamsport, Pennsylvania 17701. This document also may be examined at the Office of Regional Counsel, ANE-7, 12 New England Executive Park, Burlington, Massachusetts 01803.
This amendment becomes effective August 25, 1983.
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82-16-03: 82-16-03 FOKKER B.V.: Amendment 39-4425. Applies to Model F28 Series 1000 and 4000 airplanes, certificated in all categories, serial numbers as indicated below. Note: Some serial numbers listed may actually be 2000, 3000, 5000, or 6000 airplanes that are not presently eligible for U.S. certification. If so, those serial numbers may be disregarded insofar as this AD is concerned.
1. Unless already accomplished, accomplish the following within the time specified in each paragraph below after the effective date of this AD.
A. Applies to airplanes with serial numbers (S/N's) 11003 through 11052, 11054 through 11061, and 11991 through 11993 when equipped with Robert Shaw oxygen system. Compliance required within the next 100 hours time in service. To preclude severe loss of oxygen, install placards in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/11-20, Revision 2, dated January 14, 1974.
B. Applies to airplanes with S/N's 11042 through 11069. Compliance required within the next 100 hours time in service. To preclude electrical failure, rework the backup ring of the pressure bung between the stub wing and the cabin in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/24-17 dated October 19, 1973.
C. Applies to airplanes with S/N's 11003 through 11055, and 11991 through 11993. Compliance required within the next 100 hours time in service. To preclude electrical failure, inspect and relocate the cable loom in the horizontal stabilizer bullet fairing in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/24-22 dated March 20, 1974.
D. Applies to airplanes with S/N's 11122 through 11142. Compliance required within the next 100 hours time in service. To prevent relay sensitivity to voltage spikes, disturbed timing, and inadvertent energizing of certain relays with time delay, install improved time delay relays in accordance with Part III of the Accomplishment Instructions of Fokker Service Bulletin F28/24-27, Revision 1, dated March 14, 1979.
E. Applies to airplanes with S/N's 11003 to 11145, 11147, 11150, 11151, 11991, and 11992. Compliance required within the next 500 hours time in service. To preclude electrical failure, inspect and relocate cable looms in designated areas of concern in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/24-31 dated October 10, 1979.
F. Applies to airplanes with S/N's 11003 through 11053, and 11991 through 11993. Compliance required within the next 500 hours time in service. To provide necessary cabin safety, replace the hat rack panels in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/25-35, Revision 1, dated November 22, 1976.
G. Applies to airplanes with S/N's 11003 through 11052, and 11991 through 11994 when equipped with pilot and copilot seats with part numbers E173213, E173214, E171755, and E171756. Compliance required within the next 100 hours time in service. To prevent unwanted movement of the backrest, inspect and modify the pilot and copilot seat backrest adjustment mechanism in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/25-38 dated June 16, 1972.
H. Applies to airplanes with S/N's 11017 through 11031, and 11033 through 11049 when equipped with galley door mounted Walter Kidde escape chutes (slides). Compliance required within the next 100 hours time in service. To preclude failure during emergency egress, secure the attachment bar lock pin with lock wire (safety wire) in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/25-41 dated September 22, 1972.
I. Applies to airplanes with S/N's 11080 through 11086, and 11088 through 11109 and to airplanes with S/N's 11003 through 11079, and 11087 when modified in accordance with Fokker Service Bulletin F28/25-52 with modification kits delivered by Fokker before September 1, 1976. Compliance required within 100 hours time in service. To prevent unwanted movement of the pilot and copilot seats, inspect and replace the seat track lock stop blocks in accordance with Parts I and II of the Accomplishment Instructions of Fokker Service Bulletin F28/25-71 dated September 6, 1976. Note: Parts I and II of Fokker Service Bulletin incorporate by reference and consist of Ipeco Service Bulletins A001-25-A2 dated July 30, 1976, and A001- 25-2 dated August 10, 1976, respectively.
J. Applies to airplanes with S/N's 11111, 11112, 11114 through 11116, 11120, 11122, 11123, and 11126. Compliance required within the next 500 hours time in service. To preclude obstruction of the left and right hand rear overwing emergency exits, remove the rear emergency escape belts in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/25-75 dated February 15, 1981. An additional escape route must be provided concurrently with this change in accordance with paragraph L below.
K. Applies to airplanes with S/N's 11080 through 11086, and 11088 through 11143 and to airplanes with S/N's 11003 through 11079, 11087, 11991, and 11992 when modified in accordance with Fokker Service Bulletin F28/25-52. Compliance required within the next 100 hours time in service. To prevent unwanted movement of the pilot and copilot seats, inspect and install larger bolts to secure the seat track lock stop in accordance with Parts I and II of the Accomplishment Instructions of Fokker Service Bulletin F28/25-82 dated January 1, 1979. Note: Parts I and II of Fokker Service Bulletin incorporate by reference and consist of Ipeco Service Bulletin A001-25-3 dated November 1, 1978.
L. Applies to airplanes with S/N's 11111, 11112, 11114 through 11116, 11118, 11120 through 11123, 11126 through 11128, 11130, 11133, 11135, 11138 through 11142, 11144, and 11148. Compliance required within the next 500 hours time in service. Tofacilitate emergency egress, establish an additional escape route via the wing trailing edge in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/25-86, Revision 1, dated November 6, 1981. Note: The disparity of serial numbers with those of related paragraph J above is due to the fact that the change was incorporated on certain airplanes prior to delivery from the factory.
M. Applies to airplanes with S/N's 11003 to 11022, and 11991 to 11992. Compliance required within the next 100 hours time in service. To preclude damage to electrical cable looms to the flap asymmetry synchro assemblies, relocate cable routing and install protection in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-68 dated June 23, 1972.
N. Applies to airplanes with S/N's 11003 through 11041, and 11991 through 11994 modified in accordance with Fokker Service Bulletin F28/29-10. Compliance required within the next 100 hours time in service. To prevent separation of the drain tube from the adaptor, which makes it impossible to completely drain the gas side of the accumulator, install adaptors with metal drain tubes in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/29-21 dated August 17, 1971.
O. Applies to airplanes with S/N's 11003 through 11101, and 11991 through 11993. Compliance required within the next 100 hours time in service. To prevent improper functioning of the antiskid system due to loose wheel speed generators, install generator support rings in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/32-117 dated January 5, 1976.
P. Applies to airplanes with S/N's 11003 through 11046, 11048 through 11081, 11083, 11085 through 11101, 11103, 11105 through 11107, 11991, and 11992 when modified in accordance with Fokker Service Bulletin F28/32-116 and to airplanes with S/N's 11047, 11082, 11084, 11102, 11104, and 11108 through 11141.Compliance required within the next 500 hours time in service. To preclude antiskid system malfunction, replace the time delay relays in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/32-127 dated March 14, 1979.
Q. Applies to airplanes with S/N's 11003 through 11066, and 11991 through 11993. Compliance required within the next 500 hours time in service. To ensure that lighting for all instruments remains available in the event one AC bus fails, modify the electrical system in accordance with Fokker Service Bulletin F28/33-11, Revision 2, dated April 4, 1975.
R. Applies to airplanes with S/N's 11003 through 11070, and 11991 through 11993. Compliance required within the next 500 hours time in service. To prevent smoke in cockpit due to burning out of ballast transformers, relocate the ballast transformers in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/33-16 dated March 20, 1974.
S. Applies toairplanes with S/N's 11006, 11014 to 11020, 11023, 11024, and 11991. Compliance required within the next 100 hours time in service. To prevent compass system flag warning showing on wrong course indicator, correct installation in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/34-14, Revision 2, dated January 27, 1972.
2. Alternate means of compliance with this AD which provide an equivalent level of safety may be used when approved by the Chief, Seattle Area Aircraft Certification Office, FAA Northwest Mountain Region.
3. 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.
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).
This amendment becomes effective August 30, 1982.
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