444 

14 CFR Ch. I (1–1–19 Edition) 

Pt. 25, App. I 

(a) The Instructions for Continued Air-

worthiness must contain a section titled Air-
worthiness Limitations that is segregated 
and clearly distinguishable from the rest of 
the document. This section must set forth— 

(1) Each mandatory modification time, re-

placement time, structural inspection inter-
val, and related structural inspection proce-
dure approved under § 25.571. 

(2) Each mandatory replacement time, in-

spection interval, related inspection proce-
dure, and all critical design configuration 
control limitations approved under § 25.981 
for the fuel tank system. 

(3) Any mandatory replacement time of 

EWIS components as defined in section 
25.1701. 

(4) A limit of validity of the engineering 

data that supports the structural mainte-
nance program (LOV), stated as a total num-
ber of accumulated flight cycles or flight 
hours or both, approved under § 25.571. Until 
the full-scale fatigue testing is completed 
and the FAA has approved the LOV, the 
number of cycles accumulated by the air-
plane cannot be greater than 

1

⁄

2

the number 

of cycles accumulated on the fatigue test ar-
ticle. 

(5) Each mandatory replacement time, in-

spection interval, and related inspection and 
test procedure, and each critical design con-
figuration control limitation for each light-
ning protection feature approved under 
§ 25.954. 

(b) 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.’’ 

H25.5

Electrical Wiring Interconnection Sys-

tem (EWIS) Instructions for Continued Air-
worthiness. 

(a) The applicant must prepare Instruc-

tions for Continued Airworthiness (ICA) ap-
plicable to EWIS as defined by § 25.1701 that 
are approved by the FAA and include the fol-
lowing: 

(1) Maintenance and inspection require-

ments for the EWIS developed with the use 
of an enhanced zonal analysis procedure that 
includes: 

(i) Identification of each zone of the air-

plane. 

(ii) Identification of each zone that con-

tains EWIS. 

(iii) Identification of each zone containing 

EWIS that also contains combustible mate-
rials. 

(iv) Identification of each zone in which 

EWIS is in close proximity to both primary 

and back-up hydraulic, mechanical, or elec-
trical flight controls and lines. 

(v) Identification of— 
(A) Tasks, and the intervals for performing 

those tasks, that will reduce the likelihood 
of ignition sources and accumulation of com-
bustible material, and 

(B) Procedures, and the intervals for per-

forming those procedures, that will effec-
tively clean the EWIS components of com-
bustible material if there is not an effective 
task to reduce the likelihood of combustible 
material accumulation. 

(vi) Instructions for protections and cau-

tion information that will minimize con-
tamination and accidental damage to EWIS, 
as applicable, during performance of mainte-
nance, alteration, or repairs. 

(2) Acceptable EWIS maintenance prac-

tices in a standard format. 

(3) Wire separation requirements as deter-

mined under § 25.1707. 

(4) Information explaining the EWIS iden-

tification method and requirements for iden-
tifying any changes to EWIS under § 25.1711. 

(5) Electrical load data and instructions for 

updating that data. 

(b) The EWIS ICA developed in accordance 

with the requirements of H25.5(a)(1) must be 
in the form of a document appropriate for 
the information to be provided, and they 
must be easily recognizable as EWIS ICA. 
This document must either contain the re-
quired EWIS ICA or specifically reference 
other portions of the ICA that contain this 
information. 

[Amdt. 25–54, 45 FR 60177, Sept. 11, 1980, as 
amended by Amdt. 25–68, 54 FR 34329, Aug. 18, 
1989; Amdt. 25–102, 66 FR 23130, May 7, 2001; 
Amdt. 25–123, 72 FR 63408, Nov. 8, 2007; Amdt. 
25–132, 75 FR 69782, Nov. 15, 2010; Doc. No. 
FAA–2014–1027, Amdt. No. 25–146, 83 FR 47557, 
Sept. 20, 2018] 

A

PPENDIX

I 

TO

P

ART

25—I

NSTALLATION

 

OF AN

A

UTOMATIC

T

AKEOFF

T

HRUST

 

C

ONTROL

S

YSTEM

(ATTCS) 

I25.1

General. 

(a) This appendix specifies additional re-

quirements for installation of an engine 
power control system that automatically 
resets thrust or power on operating engine(s) 
in the event of any one engine failure during 
takeoff. 

(b) With the ATTCS and associated sys-

tems functioning normally as designed, all 
applicable requirements of Part 25, except as 
provided in this appendix, must be met with-
out requiring any action by the crew to in-
crease thrust or power. 

I25.2

Definitions. 

(a) 

Automatic Takeoff Thrust Control System 

(ATTCS). 

An ATTCS is defined as the entire 

automatic system used on takeoff, including 
all devices, both mechanical and electrical, 

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