186 

14 CFR Ch. I (1–1–19 Edition) 

Pt. 60, App. A 

E

ND

I

NFORMATION

 

B

EGIN

QPS R

EQUIREMENTS

 

C. Engine and Airframe Icing Evaluation (Table 

A1A, Section 2.j.) 

1. Applicability: This section applies to all 

FSTDs that are used to satisfy training re-
quirements for engine and airframe icing. 
New general requirements and objective re-
quirements for simulator qualification have 
been developed to define aircraft specific 
icing models that support training objectives 
for the recognition and recovery from an in- 
flight ice accretion event. 

2. General Requirements: The qualification 

of engine and airframe icing consists of the 
following elements that must be considered 
when developing ice accretion models for use 
in training: 

a. Ice accretion models must be developed 

to account for training the specific skills re-
quired for recognition of ice accumulation 
and execution of the required response. 

b. Ice accretion models must be developed 

in a manner to contain aircraft specific rec-
ognition cues as determined with aircraft 
OEM supplied data or other suitable analyt-
ical methods. 

c. At least one qualified ice accretion 

model must be objectively tested to dem-
onstrate that the model has been imple-
mented correctly and generates the correct 
cues as necessary for training. 

3. Statement of Compliance: The SOC as 

described in Table A1A, Section 2.j. must 
contain the following information to support 
FSTD qualification of aircraft specific ice 
accretion models: 

a. A description of expected aircraft spe-

cific recognition cues and degradation ef-
fects due to a typical in-flight icing encoun-
ter. Typical cues may include loss of lift, de-
crease in stall angle of attack, changes in 
pitching moment, decrease in control effec-
tiveness, and changes in control forces in ad-
dition to any overall increase in drag. This 
description must be based upon relevant 
source data, such as aircraft OEM supplied 
data, accident/incident data, or other accept-
able data sources. Where a particular air-
frame has demonstrated vulnerabilities to a 
specific type of ice accretion (due to acci-
dent/incident history) which requires specific 
training (such as supercooled large-droplet 
icing or tailplane icing), ice accretion mod-
els must be developed that address the train-
ing requirements. 

b. A description of the data sources uti-

lized to develop the qualified ice accretion 
models. Acceptable data sources may be, but 
are not limited to, flight test data, aircraft 
certification data, aircraft OEM engineering 
simulation data, or other analytical methods 
based upon established engineering prin-
ciples. 

4. Objective Demonstration Testing: The 

purpose of the objective demonstration test 
is to demonstrate that the ice accretion 
models as described in the Statement of 
Compliance have been implemented cor-
rectly and demonstrate the proper cues and 
effects as defined in the approved data 
sources. At least one ice accretion model 
must be selected for testing and included in 
the Master Qualification Test Guide (MQTG). 
Two tests are required to demonstrate en-
gine and airframe icing effects. One test will 
demonstrate the FSTDs baseline perform-
ance without icing, and the second test will 
demonstrate the aerodynamic effects of ice 
accretion relative to the baseline test. 

a. 

Recorded Parameters: 

In each of the two 

required MQTG cases, a time history record-
ing must be made of the following param-
eters: 

i. Altitude; 
ii. Airspeed; 
iii. Normal Acceleration; 
iv. Engine Power/settings; 
v. Angle of Attack/Pitch attitude; 
vi. Bank Angle; 
vii. Flight control inputs; 
viii. Stall warning and stall buffet onset; and 
ix. Other parameters as necessary to dem-

onstrate the effects of ice accretions. 

b. 

Demonstration maneuver: 

The FSTD spon-

sor must select an ice accretion model as 
identified in the SOC for testing. The se-
lected maneuver must demonstrate the ef-
fects of ice accretion at high angles of attack 
from a trimmed condition through approach 
to stall and ‘‘full’’ stall as compared to a 
baseline (no ice buildup) test. The ice accre-
tion models must demonstrate the cues nec-
essary to recognize the onset of ice accretion 
on the airframe, lifting surfaces, and engines 
and provide representative degradation in 
performance and handling qualities to the 
extent that a recovery can be executed. Typ-
ical recognition cues that may be present de-
pending upon the simulated aircraft include: 

i. Decrease in stall angle of attack; 
ii. Increase in stall speed; 
iii. Increase in stall buffet threshold of per-

ception speed; 

iv. Changes in pitching moment; 
v. Changes in stall buffet characteristics; 
vi. Changes in control effectiveness or con-

trol forces; and 

vii. Engine effects (power variation, vibra-

tion, etc.); 

The demonstration test may be conducted by 
initializing and maintaining a fixed amount 
of ice accretion throughout the maneuver in 
order to consistently evaluate the aero-
dynamic effects. 

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