79-13-01 BEECH: Amendment 39-3504. Applies to Models C50, D50, D50A, D50B, D50C, D50E, E50, F50, G50, H50, and J50 airplanes modified in accordance with STC SA76SW certified in all categories.
Compliance is required as indicated unless already accomplished.
To reduce the possibility of powerplant fire occurrence and improve powerplant fire containment and detection capabilities, accomplish the following:
a. Within 25 hours time-in-service after the effective date of this Amendment, incorporate into the existing Airplane Flight Manual, the temporary Airplane Flight Manual Supplement Included in this AD as Figure 1 or Excalibur Aviation Flight Manual Supplement dated May 31, 1979, or later approved revision.
b. Within 100 hours time-in-service after the effective date of this Amendment, accomplish items (1), (2), (3), and (4) below, except that this compliance time may be extended to 200 hours time-in-service if the inspection of components forward of the firewall required by AD 79-01-02 is accomplished at intervals no greater than 50 hours time-in-service during this compliance time extension:
(1) Replace existing flexible fuel, oil, hydraulic, and fuel or oil vapor carrying hose assemblies except engine breather and drain lines in the engine compartment with equivalent length and diameter hoses having strength and fire resistance qualities meeting FAA Technical Standard Order C53A, Type C or D, or as specified below. Hose assemblies fabricated or Stratoflex Type 111 or 130 hose covered by fire resistant sleeve, Stratoflex Type 2650 or 2607, or Aeroquip hose Type 303 covered with fire resistant sleeve Type AE102 or 624, or an FAA-approved equivalent are acceptable. (Pressure test the hose assemblies in accordance with industry practice.)
Use old hoses as a pattern when fabricating new hoses. Caution should be exercised to assure end fittings on new hoses are equivalent to old hose end fittings. Install hoses observing the manufacturer's torque limits. Apply paint or torque putty to fittings after tightening.
(2) On airplanes having engines with the Bendix fuel injection system, after changing all engine and installation fuel system hoses but prior to connecting the hose at the fuel injector nozzle located at the top of the induction housing, cap this hose at the nozzle end, select main tanks, turn main boost pumps ON, place mixture controls in rich position, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck prior to installing hose on nozzle fittings.
(3) On airplanes other than those specified in paragraph b(2) above, after changing all installation fuel system hoses, with mixture control in "cut off" position, select main tanks, turn main boost pump ON, and check all fuel carrying lines and fittings for leakage. Correct any leaks detected and recheck.
(4) After determining that no fuel is trapped in the induction system, conduct the run-up specified in Figure 1 and inspect all hoses and fittings for signs of fuel or oil leakage.
c. On or before October 19, 1979, install continuous type fire detector systems in the engine compartment and wheel wells in accordance with the Beech Service Kit No. 80-9010, or the Shadin Kit No. 2125-1, with revisions as covered by Excalibur Aviation Company Service Bulletin No. 79-01.
d. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Southwest Region.
Beechcraft Service Instructions No. 0999, Shadin Report No. 2125, and Excalibur Aviation Company Service Bulletin 79-01 or later approved revisions referenced herein cover the subject matter of this AD.
This amendment becomes effective July 5, 1979.
FIGURE 1
TEMPORARY AIRPLANE FLIGHT MANUAL SUPPLEMENT
FOR BEECH MODEL 50 SERIES AIRPLANES
(AD 79-13-01 requires this supplement to remain in the airplane flight manual until replaced by Excalibur Aviation Company Flight Manual Supplement dated May 31, 1979, or later approved revisions.)
Model N- S/N
In addition to the presently specified preflight procedures, prior to first flight of each day, accomplish the following:
1. Start both engines and operate at 1500 RPM. After the oil pressures stabilize, shut down the engines using the mixture control.
2. Open the cowl doors on both sides of the engines and check all engine compartment fluid hoses and fittings for indications of fluid (fuel or oil) leakage. Check the wheel wells for these same conditions using a flashlight or supplemental light as necessary to provide adequate illumination of the area.
3. Correct any leak detected and secure cowl doors.
4. Record in Airplane Maintenance Records.