84-13-01 FAIRCHILD (SWEARINGEN): Amendment 39-4885. Applies to Models SA226- TC, (S/N 398 and up); SA227-AC; SA227-AT and SA227-TT (all serial numbers) airplanes certificated in any category.
NOTE: The model prefix has been omitted from serial numbers listed in this AD to simplify the AD. Use the sequential number to determine AD applicability.
Compliance: Required as indicated, unless already accomplished.
To prevent cockpit fires, accomplish the following:
(a) On all applicable models and serial numbers, within the next 50 hours time-in- service after the effective date of this AD, modify and inspect the generator control junction box (J- box) and wire terminations in accordance with Fairchild SB's 24-003 (SA227 series) dated March 21, 1983, or 24-021 (SA226-TC) dated March 21, 1983.
(b) Within 200 hours time-in-service since new or the last inspection per AD 84-05-01 or 50 hours time-in-service after the effective date of this AD, whichever occurs later, and within each 200 hours time-in-service thereafter.
(1) On Models SA226-TC (S/N 398 and up) and SA227-AC, -AT, -TT (S/Ns 406, 415, 416 and 420 through 583) airplanes;
(i) Verify that all 3 flammable fluid external drains are open.
(ii) Feel the bottom of flammable fluid bag for pockets of oil. If oil is detected, push up lower spot in bag toward either the right or left drain. Verify that oil comes out of one or all of the drains.
Temporarily place rags in lower left bag just forward of the open area to prevent fluid from draining into belly of aircraft.
Remove instruments as necessary to allow access to the bag. Unzip a small portion of the bag to determine cause of leak. Correct cause of leak. Clean bag with rags using Brulin Super 816 detergent in 3 parts water to 1 part detergent or an equivalent industrial cleaner (detergent) per AMS 1526 or 1547 or 1550.
Use rags to clean out any residue that may havecollected in the lower left bag. Close all opened flammable fluid protection bags and handshape the bags to encourage flow of leakage toward the bag drains.
(iii) The inspections required by paragraph (b)(1)(i) and (ii) above are not required when improved brake master cylinders are incorporated per Fairchild Service Bulletins 226-32-046 applicable to the Models 226 series airplanes or 32-013, Option 2, applicable to the Model 227 series airplanes.
(2) On Models SA226-TC (S/N TC-398 thru TC-419) and SA227-AC, -AT, and -TT (S/N 406, 415, 416 and 420 thru 609 except AC-580, AC-582 and AC-583) airplanes;
(i) Visually check oxygen lines for separation from moving components and for leakage using MIL-L-25567B leak detector solution or equivalent as specified in Fairchild Maintenance Manual. Minimum clearance between oxygen lines and all moving parts must be at least 2 inches. Give particular attention to the fittings in the vicinity of the cockpit side panelsand instrument panel area and the fittings on the oxygen supply line from the oxygen bottle to the cockpit. If leaks are found, prior to further flight, correct as necessary. See Fairchild Maintenance Manual Section 35-00-06 (SA226) and Section 35-00-05 (SA227) for proper maintenance of lines and fittings.
NOTE: FAA Advisory Circular 43.13-1A, Chapter 10, paragraph 393, Chapter 8, paragraph 363, contains additional guidance pertaining to these inspections and corrective action.
(ii) The inspections required by paragraph (b)(2)(i) above are not required when Fairchild Service Bulletin SB 226-35-002, 227-35-003 or 227-35-004 as applicable to the Models 226 or 227 series airplanes are incorporated.
(3) On Models SA226-TC (S/Ns 398 and up) and SA227 (all models and S/Ns) airplanes not equipped with optional antiskid system;
(i) Visually inspect the brake reservoir vent area located on the forward pressure bulkhead in front of the pilot for signs of hydraulic fluid contamination.
(ii) Before further flight, clean or replace as necessary any hydraulic fluid-contaminated structure, insulation, or soundproofing.
(c) On Models SA226-TC (S/N TC398 and up) and Models SA227-AC, -AT, -TT (S/Ns 415, 416, and 420 thru 599) airplanes, within 200 hours time since new or within 50 hours time-in-service after the effective date of this AD whichever occurs later, visually inspect the electrical wires and their supports 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 including hydraulic and oxygen lines or structure. It is desirable to maintain a 6-inch clearance between oxygen tubing and electrical wires. If this is not possible, fasten all electrical wires securely so that they cannot come to within 2 inches of oxygen tubing. If 2 inches cannot be maintained, reroute oxygen line or wires as necessary to get the maximum possible clearance and then add additional support and/or "butterfly" clamp as necessary to prevent contact between oxygen lines and electrical wires bundles. Accomplishment of paragraph (a)(4) of AD 84-05-01 satisfies this requirement.
(d) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished.
(e) 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.
(f) An equivalent method of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, Southwest Region, FAA, Fort Worth, Texas 76101; telephone (817) 877-2070.
This AD supersedes AD 84-05-01, Amendment 39-4822.
This Amendment 39-4885 becomes effective on July 5, 1984.