654 

14 CFR Ch. I (1–1–19 Edition) 

§ 29.1305 

including gearboxes necessary for rotor 
phasing; 

(11) A gas temperature indicator for 

each turbine engine; 

(12) A gas producer rotor tachometer 

for each turbine engine; 

(13) A tachometer for each engine 

that, if combined with the applicable 
instrument required by paragraph 
(a)(14) of this section, indicates rotor 
r.p.m. during autorotation. 

(14) At least one tachometer to indi-

cate, as applicable— 

(i) The r.p.m. of the single main 

rotor; 

(ii) The common r.p.m. of any main 

rotors whose speeds cannot vary appre-
ciably with respect to each other; and 

(iii) The r.p.m. of each main rotor 

whose speed can vary appreciably with 
respect to that of another main rotor; 

(15) A free power turbine tachometer 

for each turbine engine; 

(16) A means, for each turbine engine, 

to indicate power for that engine; 

(17) For each turbine engine, an indi-

cator to indicate the functioning of the 
powerplant ice protection system; 

(18) An indicator for the filter re-

quired by § 29.997 to indicate the occur-
rence of contamination of the filter to 
the degree established in compliance 
with § 29.955; 

(19) For each turbine engine, a warn-

ing means for the oil strainer or filter 
required by § 29.1019, if it has no bypass, 
to warn the pilot of the occurrence of 
contamination of the strainer or filter 
before it reaches the capacity estab-
lished in accordance with § 29.1019(a)(2); 

(20) An indicator to indicate the func-

tioning of any selectable or control-
lable heater used to prevent ice clog-
ging of fuel system components; 

(21) An individual fuel pressure indi-

cator for each engine, unless the fuel 
system which supplies that engine does 
not employ any pumps, filters, or other 
components subject to degradation or 
failure which may adversely affect fuel 
pressure at the engine; 

(22) A means to indicate to the 

flightcrew the failure of any fuel pump 
installed to show compliance with 
§ 29.955; 

(23) Warning or caution devices to 

signal to the flightcrew when ferro-
magnetic particles are detected by the 

chip detector required by § 29.1337(e); 
and 

(24) For auxiliary power units, an in-

dividual indicator, warning or caution 
device, or other means to advise the 
flightcrew that limits are being exceed-
ed, if exceeding these limits can be haz-
ardous, for— 

(i) Gas temperature; 
(ii) Oil pressure; and 
(iii) Rotor speed. 
(25) For rotorcraft for which a 30-sec-

ond/2-minute OEI power rating is re-
quested, a means must be provided to 
alert the pilot when the engine is at 
the 30-second and 2-minute OEI power 
levels, when the event begins, and 
when the time interval expires. 

(26) For each turbine engine utilizing 

30-second/2-minute OEI power, a device 
or system must be provided for use by 
ground personnel which— 

(i) Automatically records each usage 

and duration of power at the 30-second 
and 2-minute OEI levels; 

(ii) Permits retrieval of the recorded 

data; 

(iii) Can be reset only by ground 

maintenance personnel; and 

(iv) Has a means to verify proper op-

eration of the system or device. 

(b) For category A rotorcraft— 
(1) An individual oil pressure indi-

cator for each engine, and either an 
independent warning device for each 
engine or a master warning device for 
the engines with means for isolating 
the individual warning circuit from the 
master warning device; 

(2) An independent fuel pressure 

warning device for each engine or a 
master warning device for all engines 
with provision for isolating the indi-
vidual warning device from the master 
warning device; and 

(3) Fire warning indicators. 
(c) For category B rotorcraft— 
(1) An individual oil pressure indi-

cator for each engine; and 

(2) Fire warning indicators, when fire 

detection is required. 

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as 
amended by Amdt. 29–3, 33 FR 970, Jan. 26, 
1968; Amdt. 29–10, 39 FR 35463, Oct. 1, 1974; 
Amdt. 29–26, 53 FR 34219, Sept. 2, 1988; Amdt. 
29–34, 59 FR 47768, Sept. 16, 1994; Amdt. 29–40, 
61 FR 21908, May 10, 1996; 61 FR 43952, Aug. 27, 
1996] 

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