80-13-02 GRUMMAN AIRCRAFT CORPORATION: Amendment 39-3800. Applies to model G-73 airplanes which have Pratt and Whitney R1340 engines installed, certificated in all categories.
Compliance is required as indicated unless already accomplished.
To reduce the possibility of powerplant fires and to improve the powerplant fire containment, detection, and extinguishing capabilities, accomplish the following:
(a) Within the next ten hours time in service after the effective date of this AD, fabricate and install on the instrument panel and in full view of the pilot an emergency procedures placard using not less than 3/32-inch high letters, which reads as follows:
ENGINE FIRE EMERGENCY PROCEDURES
(1) FUEL SELECTOR - OFF.
(2) FIRE SHUTOFF T-HANDLE - PULL.
(3) MIXTURE CONTROL - IDLE CUTOFF.
(4) PROPELLER - FEATHER.
(5) COWL FLAPS - CLOSE.
(6) FUEL BOOSTER PUMP - OFF.
(7) IGNITION SWITCH - OFF.
(8) FIRE EXTINGUISHER SWITCH - SELECT AND ACTUATE.
(b) Within the next 50 hours time in service after the effective date of this AD, using the practices and procedures identified by AC 43-13-1A, install two yellow caution lights, one for each engine, which will illuminate when the applicable starter relay is energized. Locate these lights on the instrument panel in full view of the pilot and install a placard using not less than 3/32- inch high letters adjacent to each light which reads "STARTER ENERGIZED."
(c) Within the next 50 hours time in service after the effective date of this AD, inspect the fuel, oil, hydraulic, and propeller feathering hose assemblies and the electrical wiring harnesses forward of the fire wall and clamp or secure to insure a minimum of one-inch clearance between all wires and combustible fluid carrying hoses.
(d) Within the next 50 hours time in service after the effective date of this AD, relocate the fire warning lights to the instrument panel in front of and in full view of the pilot.(e) On or before November 15, 1980, or within the next 250 hours' time in service after the effective date of this AD, whichever occurs first, convert one-bottle fire extinguishing systems to two-bottle fire extinguishing systems in accordance with Grumman Drawing 109007 or an FAA-approved equivalent system.
(f) On or before November 15, 1980, or within the next 250 hours time in service after the effective date of this AD, whichever occurs first, replace the existing spot detector type fire detection system with a continuous loop fire detection system in accordance with McGraw- Edison STC SA2-427 as revised by their conversion drawing to install sensor cables 244-14482 and 244-12082, or an equivalent method approved by the Chief, Engineering and Manufacturing Branch, Southern Region.
(g) On or before November 15, 1980, or within the next 250 hours time in service after the effective date of this AD, whichever occurs first, replace or convert existing flexible fuel, oil, hydraulic, and propeller feathering hose assemblies in the engine compartment forward of the fire wall with equivalent length and diameter hoses having strength and fire resistant qualities meeting FAA Technical Standard Order C53A, Type C or D. Install hoses in accordance with AC 43-13-1A or the manufacturer's instructions.
(h) Make an appropriate maintenance record entry.
(i) An equivalent method of compliance may be approved by the Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southern Region.
This amendment is effective June 20, 1980.