78-11-01 BEECH: Amendment 39-3220 as amended by Amendment 39-3277 is further amended by Amendment 39-3413. Applies to E50, F50, G50, H50, J50, 65, A65, A65-8200, 65- 80, 65-A80, 65-A80-8800, 65-B80, 65-88 and 70 model airplanes certified in all categories except those modified in accordance with STCs SA444SW or SA587SW.
COMPLIANCE: 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 the next 25 hours time-in-service after June 1, 1978, install in the existing Airplane Flight Manual, the temporary airplane Flight Manual Supplement included in this AD as Figure 1, or, Beech Aircraft Company Airplane Flight Manual Supplement P/N 50-590211-31 dated May 29, 1978 or subsequent revision.
B) Within the next 100 hours time-in-service after June 1, 1978, except that this compliance time may be extended to 200 hourstime-in-service if the inspection of components forward of the firewall required by AD 77-25-01 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 of 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 hose specified in Beechcraft Service Instructions No. 0999 or later approved revisions, or an FAA- approved equivalent are acceptable except as noted below. (Pressure test the hose assemblies in accordance with industry practice.)
On airplanes having serial numbers LC-157 through LC-335, LB-1 through LB-35, and LD-135 through LD-512, replace the main oil supply hose running from the firewall to the engine with a Stratoflex Part No. 156F001-16D0200 hose assembly or Aeroquip 620100-16-0200 hose assembly or an FAA-approved equivalent.
On the Model 88 series airplanes, fabricate the hose from the engine hydraulic pump "oil out" to the firewall using high pressure type hose. Stratoflex Type 112 or Aeroquip Type 309 or FAA-approved equivalent is acceptable. Subject only these hoses to a proof pressure test of 7000 PSI and install applicable hose manufacturer's fire sleeves of types noted above.
Stratoflex Type 111 or 130 hose or Aeroquip Type 303 hose with appropriate manufacturer's fire sleeve as noted above or hose specified in Beechcraft Service Instructions No. 0999 or later approved revisions, or an FAA-approved equivalent are acceptable for all other pressurization system hoses. Engine induction system hoses and vacuum system hoses are not included in the requirements of this AD.
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 manufacturer's torque limits. The torque chart contained in Beechcraft Service Instructions No. 0999 or later approved revisions list acceptable limits. Apply paint or torque putty to fittings after tightening.
2) On airplanes having engines with 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 otherthan those specified in Paragraph B(2) above, after changing all installation fuel system hoses, with mixture control in "cut off", select main tanks, turn main boost pumps 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 runup specified in Figure 1 and inspect all hoses and fittings for signs of fuel or oil leakage.
C) On or before January 31, 1979 install continuous type fire detector systems in the engine compartment and wheel wells in accordance with Beech Service Kit 80-9010.
NOTE: The compliance date for this paragraph was established on the basis of the most accelerated schedule the vendors of the detector components can meet and the estimated number of active airplanes of the affected models. The FAA recommends that every owner place an order for the necessary modification kit as early as possible.
D) Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.
Beechcraft Service Instructions No. 0999 or later approved revisions referenced herein covers the subject matter of this AD.
Figure 1
TEMPORARY AIRPLANE FLIGHT MANUAL SUPPLEMENT
FOR BEECH MODEL 50 SERIES, 65 SERIES
A65 SERIES AND 70 AIRPLANES WITH RECIPROCATING ENGINES
(AD 78-11-01 requires this supplement to remain in the below designated airplane flight manual until replaced by Beech Aircraft Company Flight Manual Supplement P/N 50-590211-31 dated May 29, 1978, or later approved revisions.)
Model_____________ N____________ S/N ______________
In addition to the presently specified preflight procedures, prior to the 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 thecowl 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.
Amendment 39-3220 became effective June 1, 1978.
Amendment 39-3277 became effective August 17, 1978.
This amendment 39-3413 becomes effective February 6, 1979.