AD 79-01-02 R2 ACTIVE

79-01-02 R2 BEECH: Amendment 39-3385 as amended by Amendment 39-3491 is further amended by Amendment 39-3914. Applies to:

(1) Models E50, F50, G50, H50, J50, 65, A65, A65-8200, 65-80, 65-A80, 65-A80-8800, 65-B80, 65-88, and 70 airplanes except those airplanes modified in accordance with STC SA444SW or STC SA587SW, and

(2) those Models C50, D50, D50A, D50B, D50C and D50E airplanes modified per STC SA76SW.

COMPLIANCE: Required as indicated unless already accomplished.

To prevent or reduce the possibility of in-flight fires in the engine compartment, wing, nacelle and main landing gear wheel well accomplish the following:

A. MODIFICATIONS OR PARTS REPLACEMENT. Within 100 hours time-in-service after December 12, 1977, or the last inspection per AD 77-25-01, on all applicable airplanes except those exempted below:

1. Unless previously accomplished per AD 72-18-07 on Models 65 (S/Ns L-1, L-2, L-6, LF-7, LF-8 and LC-1 thru LC-239) A65 and A65-8200 (S/Ns LC-240 thru LC-335); 70 (S/Ns LB-1 thru LB-35) 65-80, 65-A80, 65-A80-8800, and 65-B80 (S/Ns LD-1 thru LD-456) and 65-88 (S/Ns LP-1 thru LP-47) airplanes.

a. Install Beech Part No. 131072 Flight Manual Supplement in the Airplane Flight Manual.

b. Install Beech P/N 50-910615-3 decal or a locally fabricated placard using 3/32" high letters on the overhead or instrument panel which reads as follows:

EMERGENCY ENGINE SHUTDOWN PROCEDURES

1. MIXTURE CONT-IDLE CUT-OFF

2. FUEL SELECTOR-OFF

3. OIL SHUT-OFF HDL-UP AND LKD

4. PROP CONTROL-FEATHERED

5. THROTTLE-FULLY OPEN

6. BOTH BOOST PUMPS-OFF

7. MAGNETO SWITCH-OFF

8. ALTNTR/GEN SWITCH OFF

2. Unless previously accomplished per AD 73-23-04 on Models 65 (S/Ns L-1, L-2, L6, LF-7 and up and LC-1 thru LC-239), A65 and A65-8200 (S/Ns LC240 through LC-335) 65-80 (S/Ns LD-1 thru LD-150 (except LD-34 and LD-46)); 65A80 and 65-A80-8800 (S/Ns LD-34, LD-46, LD-151thru LD-269); 65-B80 (S/Ns LD-270 thru LD-475); 70 (S/Ns LB-1 and up) E50 (S/Ns EH-1 thru EH-70); F50 (S/Ns FH-71 thru FH-96 (except FH-94)) G50 (S/Ns GH-94, GH-97 thru GH-119); H50 (S/Ns HH-120 thru HH-149); J50 (S/Ns JH-150 and up) airplanes, except those modified per STCs SA444SW, SA76SW or SA587SW install Beech Nacelle Interior Fire Seal Kit No. 65-9008-1.

3. Unless previously accomplished per AD 73-23-04 on Models 65-88 (S/Ns LP-1 and up (except LP-27 and LP-29)) airplanes, except those modified per STCs SA444SW, SA76SW or SA587SW install Beech Nacelle Interior Fire Seal Kit No. 65-9008-3.

4. Unless previously accomplished per AD 75-25-04 on Model 65-B80 (S/Ns LD-476 thru 502 and LD-504) airplanes, visually inspect the nacelle interior fire shield installation for the proper installation of the P/N 50-980109-5 and -7 shields in accordance with Beechcraft Service Instruction No. 0771-065 or later revision and correct as necessary in accordance with the above service instruction.

5. Unless previously accomplished per AD 76-13-03 on Model 65-88 (S/Ns LP-1 thru LP-26, LP-28 and LP-30 thru LP-47) airplanes, visually inspect the LH and RH nacelle fire shield installation in accordance with Beechcraft Service Instructions 0809-065 or later approved revision for installation of the small P/N 50-980109-5 shield above the second stage augmenter tube on the inboard side of both nacelles. If not present install this part in accordance with the above Instruction.

B. INSPECTIONS

1. Within 25 hours time-in-service after December 12, 1977, or 100 hours time-in-service after the last inspection per AD 77-25-01 and each 100 hours time-in-service thereafter, except as noted in paragraph B.2., accomplish the following:

a. Engine Compartment Inspection

Open the cowl doors and visually inspect engine and powerplant components forward of the firewall as indicated.

i) Drain plugs, filters and strainers for security, leakage and dirt accumulation.

ii) Engine cylinders for cracks, abnormal leakage and security of hold down nuts.

NOTE: Minor oil seepage stains at engine parting lines, rocker box covers, and push rod housings are acceptable.

iii) Engine carburetion and induction system for security of attachment, evidence of leakage, deterioration and damage such as stains, chafing, cuts, bulges and cracks.

iv) Fuel and oil lines and their fittings for security as evidenced by torque paint or putty, and evidence of deterioration such as stiffness, stains, cracks, chafing, and leakage.

NOTE: Fire sleeves need not be removed for this inspection.

v) Exhaust system stacks and primary augmenters for security of attachment, integrity of supports, cracks, bulges and alignment.

vi) Drains for deterioration and blockage.

vii) Cowl and firewall for fuel and oil stains and indications of source of these stains.

viii) Firewall for missing or deteriorated grommets and open holes.

b. Nacelle and wheel well inspection:

Remove augmenter covers, open or remove access doors and inspection covers, canvas covers over fuel selectors (if installed), invertor access covers (if installed), and cover over the hydraulic driven cabin pressurization compressor (Model 65-88) and visually inspect the following components in the engine nacelles as indicated:

i) All flammable fluid lines and drain lines for deterioration, chafing against other components, other damage and fitting security.

ii) Oil tank installation including supply, return and vent lines for evidence of deterioration, leakage or damage.

iii) Fuel selector valve and hydraulic cabin pressurization system reservoir for evidence of damage, leakage and security of line fittings and mounting.

c. Fuel System Leakage Inspection:

On airplanes having engines with Bendix fuel injection system disconnect and cap the hose at the fuel injectionnozzle at the top of the induction housing, select main tanks, turn main boost pump ON, place mixture control in rich position and check all fuel carrying lines and fittings in the engine compartment and wheel well for leakage. Correct leaks detected and recheck prior to installing hose on nozzle fitting. On other airplanes, with mixture control in "cut off" select main tanks, turn main boost pump ON and check all fuel carrying lines and fittings in the engine compartment and wheel well for leakage. Correct leaks detected and recheck.

d. Wing Inspection:

i) Visually inspect the wings for fuel stains or wetness of the lower wing skin from fuel cell leakage.

ii) Remove leading edge between nacelle and fuselage and visually inspect flexible and solid flammable fluid line and electrical bundles for adequate separation.

2. Within 100 hours time-in-service since last inspection per AD 77-25-01 and each 500 hours time-in-service thereafter, on Models 65 (SerialNumber LC-163 thru LC-324); 65-80 (Serial Numbers LD-1 thru LD-150) and 65-A80 (Serial Numbers LD-151 thru LD-269, except LD-263)

a. Remove the inboard secondary augmenter and visually inspect fuel flow indicator hoses on aft side of firewall above augmenters for evidence of deterioration or chafing, tightness of fittings and line security.

3. After completion of above inspections, correct all unsatisfactory or unairworthy conditions noted and reinstall or close all door panels or access plates removed for the inspections.

C. ENGINE RUN UP AND FUEL SYSTEM FUNCTIONAL CHECK.

1. After completion of inspections required by Section B, start and warm up engines using normal procedures. Check functioning of fuel injector or carburetor idle cutoff by moving mixture controls to "idle cutoff" position and observing RPM and fuel pressure, or flow indications as appropriate, for drop. When drop is observed move mixture control back to full rich position and check for proper fuel tank selector valve operation by placing selector in "OFF" position and observe engine RPM and fuel pressure or flow indications, as appropriate, for drop. After stopping engines, open cowls and visually inspect engine compartments and nacelles for fuel or oil leakage and correct as necessary before returning airplane to service.

D. The interval for the repetitive inspection and checks set forth in Paragraphs A, B and C of this AD may be extended by 10 hours up to a maximum of 110 hours time-in-service to allow compliance at previously scheduled maintenance periods.

E. Any equivalent method of compliance with this AD must be approved by the Chief, Engineering and Manufacturing Branch, FAA, Central Region.

Beech Service Bulletins No. 66-24 or later revisions, Beech Service Bulletin No. 67-8 or later revisions, Beechcraft Service Instruction 0509-016 or later revision, Beechcraft Service Instruction No. 0771-065 or later revision, and Beechcraft Service Instructions 0809-065 or later revision pertain to this subject.

This AD supersedes the following: AD 72-18-07, Amendment 39-1512 (37 FR 18030); AD 72-18-08, Amendment 39-1513 (37 FR 18030 and 18031) as amended by Amendment 39-3152 (43 FR 9593 and 9594); AD 73-23-04, Amendment 39-1740 (38 FR 30867), as amended by Amendment 39-1771 (39 FR 2469) and 39-1813 (39 FR 13072 and 13073); AD 75-25-04, Amendment 39-2449 (40 FR 56883); AD 76-13-03, Amendment 39-2690 (41 FR 25997); and 77-25-01, Amendment 39-3092 (42 FR 61993-61995).

Amendment 39-3385 became effective January 8, 1979.

Amendment 39-3491 became effective on June 4, 1979.

This Amendment 39-3914 becomes effective on September 22, 1980.