AD 85-04-01 R1 ACTIVE

85-04-01 R1 FAIRCHILD: Amendment 39-5005 as amended by Amendment 39-5138. Applies to Models SA226-T, SA226-T(B), SA226-AT (all serial numbers) and Model SA226-TC (all serial numbers below S/N TC398) airplanes certificated in any category.

Compliance: Required as indicated, unless already accomplished.

To prevent cockpit fires and hydraulic failures by increasing the fatigue resistance of certain hydraulic lines and replacing nonmetallic oxygen lines with metal lines, accomplish the following:

(a) Within the next 25 hours time-in-service, after the effective date of this AD on airplanes not previously inspected per AD 83-19-02 or within 200 hours time-in-service after the last inspection per AD 83-19-02 and within each 200 hours time-in-service thereafter:

(1) Visually inspect the hydraulic and oxygen lines for leakage in the vicinity of the side panel and behind the instrument panel on both sides of the aircraft. Apply maximum pilot effort to the brakepedals while inspecting the brake lines.

(2) Visually inspect, in the forward-pressure bulkhead area, for hydraulic fluid contamination from the brake reservoir vent.

(3) Before further flight, clean or replace any hydraulic fluid-contaminated structure, material or equipment and replace any lines or tubing which leak or have stress cracks which could cause future leaks found during inspection per paragraphs (a)(1) and (2).

NOTE: Follow FAA Advisory Circular 43.13-1A, Chapter 10, paragraph 393, and Chapter 8, paragraph 363, when accomplishing these inspections and corrective action required by paragraphs (a)(1), (2), and (3).

(4) Visually inspect the electrical wires in the vicinity of the cockpit side panels and behind the instrument panel on both sides of the aircraft for contact or inadequate clearance between the wires and adjacent components, especially hydraulic and oxygen lines. Determine that the wire bundles near the rudder pedals have adequateseparation with the pedals in their extreme positions. Prior to further flight, add additional supports or reroute, as necessary, to prevent wire contact or chafing which may damage the wire insulation, and clean any contamination from the bundles.

NOTE: Follow FAA Advisory Circular 43.13-1A, Chapter 11, when accomplishing these inspections and corrective action.

(b) Within the next 25 hours time-in-service after the effective date of this AD unless already accomplished:

(1) Inspect wires and wire terminations within and below the generator control junction box (J-box) and install phenolic insulator on side of J-box and spiral wrap on wires in accordance with Fairchild Service Bulletin 24-021 dated March 21, 1983.

(2) On Aircraft Models SA226-T (S/Ns T201 through T287); SA226-AT (S/Ns AT001 through AT066); and SA226-TC (S/Ns TC201 through TC247) in which MIL-H- 5606 hydraulic fluid is used, drain and purge the main hydraulic and brake system reservoirs and refill these reservoirs with MIL-H-83282 fluid. Change the placards on both reservoirs to specify MIL-H-83282 fluid.

(c) On or before December 31, 1985, modify Model SA226 airplanes in accordance with the following:

(1) On Models SA226-T (S/N's T201 through T275, T277 through T291), SA226-T(B) (S/N's TB276, TB292 through TB417), SA226-AT (S/N's AT001 through AT074), and SA226-TC (S/N's TC201 through TC397) airplanes, modify the hydraulic system in accordance with Fairchild S/B 226-29-005 revised July 19, 1985.

NOTE: Inspect condition of cushion clamps when changing hydraulic lines and change as necessary.

(2) On Models SA226-T (S/N's T249 through T275, T227 through T291), SA226-T(B) (S/N's TB276, TB292 through TB417), SA226-AT (S/N's AT001 through AT074), and SA226-TC (S/N's TC201 through TC397) airplanes, modify the crew oxygen system in accordance with Fairchild S/B 226-35-003 revised July 19, 1985.

(d) On airplanes modified in accordance with paragraph (c) of this AD.

(1) If equipped with an anti-skid brake system, compliance with inspections required by paragraphs (a) (1), (2), and (4) of this AD is not required.

(2) If not equipped with an anti-skid brake system, compliance with inspections required by paragraph (a) (1) and (4) of this AD is not required.

(e) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.

(f) The intervals between repetitive inspections required by this AD may be adjusted up to 10 percent of the specified interval to allow accomplishing these inspections concurrent with other scheduled maintenance of the airplane.

(g) An equivalent method of compliance with this AD may be used when approved by the Manager, Aircraft Certification Division, ASW-100, Southwest Regional Office, FAA, Fort Worth, Texas 76101; Telephone (817) 624-4911, Extension 511.

This AD supersedes AD 83-19-02.

Amendment 39-5005 became effective on March 30, 1985.

This Amendment 39-5138 becomes effective October 28, 1985.