200
14 CFR Ch. I (1–1–19 Edition)
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.
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
PPENDIX
O
TO
P
ART
25—S
UPERCOOLED
L
ARGE
D
ROP
I
CING
C
ONDITIONS
A
UTHORITY
: 49 U.S.C. 106(f), 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.
(c)
Installation of engines of not more than
1,830 cubic inches displacement and not having
a certificated take-off rating of more than 1,350
horsepower.
Engines of not more than 1,830
cubic inches displacement and not having a
certificated take-off rating of more than
1,350 horsepower which necessitate a major
modification of redesign of the engine instal-
lation may be installed, if the engine fire
prevention and fire protection are equivalent
to that on the prior engine installation.
(d)
Installation of engines of more than 1,830
cubic inches displacement or having certificated
take-off rating of more than 1,350 horsepower.
Engines of more than 1,830 cubic inches dis-
placement or having certificated take-off
rating of more than 1,350 horsepower may be
installed if compliance is shown with the en-
gine installation requirements of Part 4b:
Provided,
That where literal compliance with
the engine installation requirements of Part
4b is extremely difficult to accomplish and
would not contribute materially to the ob-
jective sought, and the Administrator finds
that the experience with the DC–3 or L–18
airplanes justifies it, he is authorized to ac-
cept such measures of compliance as he finds
will effectively accomplish the basic objec-
tive.
4.
Establishment of new maximum certificated
weights.
An applicant for approval of new
maximum certificated weights shall apply
for an amendment of the airworthiness cer-
tificate of the airplane and shall show that
the weights sought have been established,
and the appropriate manual material ob-
tained, as provided in this section.
N
OTE
: Transport category performance re-
quirements result in the establishment of
maximum certificated weights for various
altitudes.
(a)
Weights–25,200 to 26,900 for the DC–3 and
18,500 to 19,500 for the L–18.
New maximum
certificated weights of more than 25,200 but
not more than 26,900 pounds for DC–3 and
more than 18,500 but not more than 19,500
pounds for L–18 airplanes may be established
in accordance with the transport category
performance requirements of either Part 4a
or Part 4b, if the airplane at the new max-
imum weights can meet the structural re-
quirements of the elected part.
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