355 

Federal Aviation Administration, DOT 

Pt. 23, App. H 

(e) Information needed to apply protective 

treatments to the structure after inspection. 

(f) All data relative to structural fasteners 

such as identification, discard recommenda-
tions, and torque values. 

(g) A list of special tools needed. 
(h) In addition, for commuter category air-

planes, the following information must be 
furnished: 

(1) Electrical loads applicable to the var-

ious systems; 

(2) Methods of balancing control surfaces; 
(3) Identification of primary and secondary 

structures; and 

(4) Special repair methods applicable to 

the airplane. 

G23.4

Airworthiness Limitations section. The 

Instructions for Continued Airworthiness 
must contain a section titled Airworthiness 
Limitations that is segregated and clearly 
distinguishable from the rest of the docu-
ment. This section must set forth each man-
datory replacement time, structural inspec-
tion interval, and related structural inspec-
tion procedure required for type certifi-
cation. If the Instructions for Continued Air-
worthiness consist of multiple documents, 
the section required by this paragraph must 
be included in the principal manual. This 
section must contain a legible statement in 
a prominent location that reads: ‘‘The Air-
worthiness Limitations section is FAA ap-
proved and specifies maintenance required 
under §§ 43.16 and 91.403 of the Federal Avia-
tion Regulations unless an alternative pro-
gram has been FAA approved.’’ 

[Amdt. 23–26, 45 FR 60171, Sept. 11, 1980, as 
amended by Amdt. 23–34, 52 FR 1835, Jan. 15, 
1987; 52 FR 34745, Sept. 14, 1987; Amdt. 23–37, 
54 FR 34329, Aug. 18, 1989] 

A

PPENDIX

H 

TO

P

ART

23—I

NSTALLATION

 

OF

A

N

A

UTOMATIC

P

OWER

R

ESERVE

 

(APR) S

YSTEM

 

H23.1, 

General. 

(a) This appendix specifies requirements 

for installation of an APR engine power con-
trol system that automatically advances 
power or thrust on the operating engine(s) in 
the event any engine fails during takeoff. 

(b) With the APR system and associated 

systems functioning normally, all applicable 
requirements (except as provided in this ap-
pendix) must be met without requiring any 
action by the crew to increase power or 
thrust. 

H23.2, 

Definitions. 

(a) 

Automatic power reserve system means 

the entire automatic system used only dur-
ing takeoff, including all devices both me-
chanical and electrical that sense engine 
failure, transmit signals, actuate fuel con-
trols or power levers on operating engines, 
including power sources, to achieve the 
scheduled power increase and furnish cockpit 
information on system operation. 

(b) 

Selected takeoff power, notwithstanding 

the definition of ‘‘Takeoff Power’’ in part 1 
of the Federal Aviation Regulations, means 
the power obtained from each initial power 
setting approved for takeoff. 

(c) 

Critical Time Interval, as illustrated in 

figure H1, means that period starting at V

1

 

minus one second and ending at the intersec-
tion of the engine and APR failure flight 
path line with the minimum performance all 
engine flight path line. The engine and APR 
failure flight path line intersects the one-en-
gine-inoperative flight path line at 400 feet 
above the takeoff surface. The engine and 
APR failure flight path is based on the air-
plane’s performance and must have a posi-
tive gradient of at least 0.5 percent at 400 
feet above the takeoff surface. 

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