spaschal on DSK3GDR082PROD with CFR

Pt. 25, App. I

14 CFR Ch. I (1-1-19 Edition)

(a) The Instructions for Continued Airworthiness must contain a section titled Airworthiness Limitations that is segregated
and clearly distinguishable from the rest of
the document. This section must set forth - 
(1) Each mandatory modification time, replacement time, structural inspection interval, and related structural inspection procedure approved under Section 25.571.
(2) Each mandatory replacement time, inspection interval, related inspection procedure, and all critical design configuration
control limitations approved under Section 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 maintenance program (LOV), stated as a total number of accumulated flight cycles or flight
hours or both, approved under Section 25.571. Until
the full-scale fatigue testing is completed
and the FAA has approved the LOV, the
number of cycles accumulated by the airplane cannot be greater than 1-2 the number
of cycles accumulated on the fatigue test article.
(5) Each mandatory replacement time, inspection interval, and related inspection and
test procedure, and each critical design configuration control limitation for each lightning protection feature approved under
Section 25.954.
(b) If the Instructions for Continued Airworthiness 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 Airworthiness Limitations section is FAA-approved and specifies maintenance required
under SectionSection 43.16 and 91.403 of the Federal Aviation Regulations, unless an alternative program has been FAA approved. - 
H25.5 Electrical Wiring Interconnection System (EWIS) Instructions for Continued Airworthiness.
(a) The applicant must prepare Instructions for Continued Airworthiness (ICA) applicable to EWIS as defined by Section 25.1701 that
are approved by the FAA and include the following:
(1) Maintenance and inspection requirements for the EWIS developed with the use
of an enhanced zonal analysis procedure that
includes:
(i) Identification of each zone of the airplane.
(ii) Identification of each zone that contains EWIS.
(iii) Identification of each zone containing
EWIS that also contains combustible materials.
(iv) Identification of each zone in which
EWIS is in close proximity to both primary

and back-up hydraulic, mechanical, or electrical 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 combustible material, and
(B) Procedures, and the intervals for performing those procedures, that will effectively clean the EWIS components of combustible material if there is not an effective
task to reduce the likelihood of combustible
material accumulation.
(vi) Instructions for protections and caution information that will minimize contamination and accidental damage to EWIS,
as applicable, during performance of maintenance, alteration, or repairs.
(2) Acceptable EWIS maintenance practices in a standard format.
(3) Wire separation requirements as determined under Section 25.1707.
(4) Information explaining the EWIS identification method and requirements for identifying any changes to EWIS under Section 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 required 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]

APPENDIX I TO PART 25 - INSTALLATION
OF AN AUTOMATIC TAKEOFF THRUST
CONTROL SYSTEM (ATTCS)
I25.1 General.
(a) This appendix specifies additional requirements 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 systems functioning normally as designed, all
applicable requirements of Part 25, except as
provided in this appendix, must be met without requiring any action by the crew to increase 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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