365
Federal Aviation Administration, DOT
Pt. 25, SFAR No. 13
1
It is not intended to waive compliance
with such airworthiness requirements as are
included in the operating parts of the Civil
Air Regulations for specific types of oper-
ation.
25.1551
Oil quantity indication.
25.1553
Fuel quantity indicator.
25.1555
Control markings.
25.1557
Miscellaneous markings and plac-
ards.
25.1561
Safety equipment.
25.1563
Airspeed placard.
A
IRPLANE
F
LIGHT
M
ANUAL
25.1581
General.
25.1583
Operating limitations.
25.1585
Operating procedures.
25.1587
Performance information.
Subpart H—Electrical Wiring
Interconnection Systems (EWIS)
25.1701
Definition.
25.1703
Function and installation: EWIS.
25.1705
Systems and functions: EWIS.
25.1707
System separation: EWIS.
25.1709
System safety: EWIS.
25.1711
Component identification: EWIS.
25.1713
Fire protection: EWIS.
25.1715
Electrical bonding and protection
against static electricity: EWIS.
25.1717
Circuit protective devices: EWIS.
25.1719
Accessibility provisions: EWIS.
25.1721
Protection of EWIS.
25.1723
Flammable fluid fire protection:
EWIS.
25.1725
Powerplants: EWIS.
25.1727
Flammable fluid shutoff means:
EWIS.
25.1729
Instructions for Continued Air-
worthiness: EWIS.
25.1731
Powerplant and APU fire detector
system: EWIS.
25.1733
Fire detector systems, general:
EWIS.
Subpart I—Special Federal Aviation
Regulations
25.1801
SFAR No. 111—Lavatory Oxygen
Systems.
A
PPENDIX
A
TO
P
ART
25
A
PPENDIX
B
TO
P
ART
25
A
PPENDIX
C
TO
P
ART
25
A
PPENDIX
D
TO
P
ART
25
A
PPENDIX
E
TO
P
ART
25
A
PPENDIX
F
TO
P
ART
25
A
PPENDIX
G
TO
P
ART
25—C
ONTINUOUS
G
UST
D
ESIGN
C
RITERIA
A
PPENDIX
H
TO
P
ART
25—I
NSTRUCTIONS FOR
C
ONTINUED
A
IRWORTHINESS
A
PPENDIX
I
TO
P
ART
25—I
NSTALLATION OF AN
A
UTOMATIC
T
AKEOFF
T
HRUST
C
ONTROL
S
YSTEM
(ATTCS)
A
PPENDIX
J
TO
P
ART
25—E
MERGENCY
E
VACU
-
ATION
A
PPENDIX
K
TO
P
ART
25—E
XTENDED
O
PER
-
ATIONS
(ETOPS)
A
PPENDIX
L
TO
P
ART
25—HIRF E
NVIRON
-
MENTS AND
E
QUIPMENT
HIRF T
EST
L
EV
-
ELS
A
PPENDIX
M
TO
P
ART
25—F
UEL
T
ANK
S
YSTEM
F
LAMMABILITY
R
EDUCTION
M
EANS
A
PPENDIX
N
TO
P
ART
25—F
UEL
T
ANK
F
LAM
-
MABILITY
E
XPOSURE
AND
R
ELIABILITY
A
NALYSIS
A
UTHORITY
: 49 U.S.C. 106(g), 40113, 44701,
44702 and 44704.
S
OURCE
: Docket No. 5066, 29 FR 18291, Dec.
24, 1964, unless otherwise noted.
S
PECIAL
F
EDERAL
A
VIATION
R
EGULATION
N
O
. 13
1.
Applicability. Contrary provisions of the
Civil Air Regulations regarding certification
notwithstanding,
1
this regulation shall pro-
vide the basis for approval by the Adminis-
trator of modifications of individual Douglas
DC–3 and Lockheed L–18 airplanes subse-
quent to the effective date of this regulation.
2.
General modifications. Except as modified
in sections 3 and 4 of this regulation, an ap-
plicant for approval of modifications to a
DC–3 or L–18 airplane which result in
changes in design or in changes to approved
limitations shall show that the modifica-
tions were accomplished in accordance with
the rules of either Part 4a or Part 4b in ef-
fect on September 1, 1953, which are applica-
ble to the modification being made:
Provided,
That an applicant may elect to accomplish a
modification in accordance with the rules of
Part 4b in effect on the date of application
for the modification in lieu of Part 4a or
Part 4b as in effect on September 1, 1953:
And
provided further, That each specific modifica-
tion must be accomplished in accordance
with all of the provisions contained in the
elected rules relating to the particular modi-
fication.
3.
Specific conditions for approval. An appli-
cant for any approval of the following spe-
cific changes shall comply with section 2 of
this regulation as modified by the applicable
provisions of this section.
(a)
Increase in take-off power limitation—
1,200 to 1,350 horsepower. The engine take-off
power limitation for the airplane may be in-
creased to more than 1,200 horsepower but
not to more than 1,350 horsepower per engine
if the increase in power does not adversely
affect the flight characteristics of the air-
plane.
(b)
Increase in take-off power limitation to
more than 1,350 horsepower. The engine take-
off power limitation for the airplane may be
increased to more than 1,350 horsepower per
engine if compliance is shown with the flight
characteristics and ground handling require-
ments of Part 4b.
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