AD 82-16-04 R1 ACTIVE

82-16-04 R1 FOKKER B.V.: Amendment 39-4426 as amended by Amendment 39-4652. 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. 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 S/N's 11003 through 11016. Compliance required within the next 100 hours time in service. In order to prevent interference of control rod with idler lever and access panel in leading edge of aileron, inspect and rectify in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-22 dated March 26, 1970.

B. Applies to airplanes with S/N's 11003 through 11162, and 11991 through 11992 if one or more flap actuators are in pre Menasco Service Bulletin 27-63 configuration. Compliance required within the next 1,000 hours time in service or 500 flights, whichever occurs first. In order to detect possible wing flap mechanical actuator ball screw failures, accomplish inspections of ball nuts and screws of the actuators in accordance with Fokker Service Bulletin F28/27-27, Revision 5, dated April 2, 1979. Note reference to Fokker Service Bulletin F28/27- 136 and Menasco Service Bulletin 27-63.

C. Applies to airplanes with S/N's 11003 through 11024, and 11991 through 11992. Compliance required within 300 hours time in service. In order to eliminate failure of the feedback link (not self aligning) on the horizontal stabilizer control unit, replace with self aligning type in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-31 dated January 18, 1971. This SB covers Abex Service Bulletin 27-10.

D. Applies toairplanes with S/N's 11003 through 11029, and 11991 through 11994. Compliance required within 100 hours time in service. In order to detect and/or prevent possible jamming of the aileron de-coupler, inspect and modify the de-coupler in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-32 dated September 21, 1970.

E. Applies to airplanes with S/N's 11003 through 11026, and 11991. Compliance required within 100 hours time in service. In order to ensure that the vane drive mechanism inside the wing flaps are in good condition, inspect and modify same in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-41 dated November 25, 1970.

F. Applies to airplanes with S/N's 11003 through 11031, and 11991 through 11994. Compliance required within 100 hours time in service. In order to prevent possible jamming of the aileron control, install an anti-rotation device on the aileron trim/feel unit in accordance with theAccomplishment Instructions of Fokker Service Bulletin F28/27-47 dated March 23, 1971.

G. Applies to airplanes with S/N's 11003 through 11035, and 11991 through 11994. Compliance required within 100 hours time in service. In order to prevent rod failure in the aileron tab drive mechanism, remove old extension rod and replace with new steel extension rod in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-55, Revision 2, dated September 15, 1972.

NOTE: In case Fokker Service Bulletin F28/27-78 (to eliminate oscillation of sequence valve in aileron tab lock and actuator assembly) is not carried out within 3,000 flights after incorporation of the steel rod, the rod should be replaced again in consultation with Fokker - BV.

H. Applies to airplanes with S/N's 11003 through 11064, and 11991 through 11993. Compliance required within 100 hours time in service. In order to prevent possible fatigue failure of the connection rod between the summing bar and servo valve of the elevator boost control unit, inspect same for friction and lubrication of the stick switch connection rod in accordance with the Accomplishment Instructions of Fokker Service Bulletin F-28/27-82A, Revision 1, dated March 1, 1973.

I. Applies to airplanes with S/N's 11003 through 11077, and 11991 through 11993. Compliance required within 500 hours time in service. In order to prevent restricted aileron control due to freeze-up of the aileron feel/trim spring unit, modify same in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-92, Revision 1, dated March 1, 1976. Note that embodiment of this service bulletin relieves the operator from the inspection as described in F28 Service Bulletin 27-122.

J. Applies to airplanes with S/N's 11003 through 11090 and 11991 through 11993, as far as equipped with units Menasco P/N 11100-7 to -33 inclusive, S/N 1-214 inclusive. Compliance required within 3,000 hours time in service. In order to prevent the ball return tube from becoming disengaged from the ball nut of the horizontal stabilizer unit, install a sleeve over the ball return tube in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-103 dated September 28, 1974. This Service Bulletin covers Menasco Service Bulletin 27- 44. Note that training flights or test flights with simulated double hydraulic failure are prohibited until the change described in Fokker Service Bulletin F28/27-103, dated September 28, 1974, has been incorporated.

K. Applies to airplanes with S/N's 11091 through 11103, as far as equipped with wing flap mechanical actuator part numbers listed in Fokker Service Bulletin F28/27-126 dated November 22, 1976. Compliance required within 500 hours time in service. In order to avoid cracking of faulty ball return tubes of the wing flap mechanical actuator, inspect and replace, if required, in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-126 dated November 22, 1976. Note that this service bulletin covers Menasco Service Bulletin 27-66.

L. Applies to airplanes with S/N's 11003 through 11162, and 11991 through 11992. Compliance required within 1,000 hours time in service for Part I and 3,000 hours time in service for Part II. Part I concerns introduction of wing flap actuators with more reliable ball nuts at wing station 1700, and Part II concerns introduction of wing flap actuators with more reliable ball nuts at wing stations 5280 and 8200. In order to prevent loss of balls through the grease nipple hole and to provide for a jamming device after failure of the ball circuit, install new wing flap actuators with more reliable ball nuts in accordance with the Accomplishment Instructions and Material Information of Fokker Service Bulletin F28/27-136 dated May 14, 1979. As indicated in that service bulletin, modification instructions and part number specifications are contained in Menasco Service Bulletin 27-78.

M. Applies to airplanes with S/N's 11003 through 11162, and 11991 through 11992. Compliance required within the next 300 hours time in service and subsequently at every 500 flights. In order to detect escape of balls from worn ball return tube located in the ball nut of the wing flap actuator, inspect ball return tubes and replace actuators as necessary in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/27-137 dated January 28, 1980.

N. Applies to airplanes with S/N's 11003 through 11037, 11040, and 11991 through 11994. Compliance required within 100 hours time in service. In order to detect and prevent imminent failure of the eye-bolt in the main landing gear actuator, inspect for proper location of bearing in eye-bolt in accordance with Accomplishment Instructions of Fokker Service Bulletin F28/32-72, Revision 2, dated November 22, 1971. Part I of this Service Bulletin concerns inspectionsof the eye-bolt bearing. Part II introduces spacers to ensure correct position of the bearing in the eye-bolt as a temporary measure pending the issue of a definitive modification by Dowty/Rotol.

O. Applies to airplanes with S/N's 11003 through 11081, and 11991 through 11993 which are equipped with the following nose gear strut part numbers: 200429002, 200429003, 200429004, and 200429005. Compliance required within 100 hours time in service. In order to detect cracks from the central slot in the down lock beak of the nose gear strut, inspect in accordance with the Accomplishment Instructions of Fokker Service Bulletin F28/32-119 dated January 26, 1976. This service bulletin refers to Dowty Rotol Service Bulletin 32-94R for method of checking for evidence of cracking.

2. Alternate means of compliance with this AD which provide an equivalent level of safety must be approved by the Manager, Seattle 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).

Amendment 39-4426 became effective August 30, 1982.

This Amendment 39-4652 becomes effective June 6, 1983.