2-2
2-2.2.1
........................... 2-3
2-2.2.5
2-9
2-9
.................. ..... 3-I
. .............................
3-1.2.4 Hazard Identification (Block
Evaluation
(Block
E) ...................
3-4
3-1.2.7 Modification
3-1.2.8 Effectiveness Evaluation
3-1.2.10 Component/System Test
.. ............................
3-1.5
3-1.7 SUBSTANTIATION
3-6
3-2.2
3-6
3-2.2.1
(FMHEA) .............. 3-9
4-1
4-2
4-5. DESIGN DRAWING REVIEWS ...................................
4-2
PROGRAM RE-
4-3
iii
p.
Report ...................... 4- 3
4-4
4-7.2.3
4-7.3 CHARACTERISTiC AND PERFORMANCE DATA ................. 4-4
4.7.3.1 Basic Aerodynam ic Data .........................................
4-4
4-7 3.3
4-7.4 WEIGHT AND BALANCE DATA ................................. 4- 5
4-7.5 STRUCTURAL DESIGN, ANALYSIS,
4-7.7 SYSTEM SAFETY DATA ......................................... 4-6
4-7.8
4-6
4-7.9.3
4-7.9.5 W ing (Compound
4-7
4-7.9.7
4-7.9.9 Landing Gear (Skid-type) ........................................ 4-8
4-7.9.10 Landing Gear (Float-type) .......................................
4-7.9.13 Flight Controls and Stability Augmentation Systems .................. 4.9
4-7.9.14 E ectrical
4-7.9.16 Avionics
4-10
4-7.9.18.1 Seats ........................................................ 4-10
4-7.9.18.2 Survival Systems
4-7.9.18.4
4-7.9.20 M iscellaneous .................................................. 4-11
4-7.12 HELICOPTER INVENTORY RECORD ............................ 4-12
4-7.13 TEST PLANS AND QUALIFICATION TEST REPORTS ............. 4-13
4-7.14 FORMAL DEMONSTRATION PLANS AND REPORTS ............. 4-14
4-7.1 ' ENGINEERING MANUFACTURING DRAWINGS
4-7.15.2
4-8 REPORTS AND DATA ............................................ 4-15
48.1 DATA SUBMITTAL, INSPECTION, AND
ACTION ................. 4-15
...................
5-4
5-2.2
L ......................................................
6-2
..............- 4
....... ......... .............. 6-4
.................. 6-6
6-7
.6-7
6-5.2.6
............. 60-7
6-11
6-Il
6-12
................. 6-12
6-9.2.3
Extrusions .. . . . . . . . . . . . . . . . . . .
. . . . . 6-15
6-10
6-12 JOINING O PE R A T IO N S..................................
....... .. 6-16
.................
6-17
6-19
6-14.1
GENERAl .......................................................
6-19
TRO
............. .................................. 6-19
7-4.2.4.1. 3 Sand and
7-4.2.4.2 Altittide ..............................
7-12
7-5.1 TRANSMISSION AND
7-5.4.1 Shafting and 7-15
8-2 FLIGHT
LOAD SURVEY
8-2.3 TEST REQUIREM
.....................
8-3.2 ENGINE VIBRATION
SURVEY PLAN ............................ 8-5
8-3.2.2 Engine Manufacturer Coordination
8-3.3.1 G
8-6
8-4.1 G EN RAL ................
8-4.3 TFST REQUIREM ENTS
PLAN ................ 8-11
8-5.3.1 Ground Tests ..............................................
8-5.5
8-6.1 GENERAL ..................................................... 8-13
8-6.2 ENGINE EXHAUST
...... ....................... . . -15
8-6.5 DOCUM ENTATION
8-7 1 GFNEFAI. ..........
8 -17
8-7.3
8-74 INSTRUM ENTATION ............................................ 8-20
8-7.5 DOCUM ENTATION .......... ............................... 8-20
8-8 CREW ENVIRONMENTAL SURVEY ................................
8-8.2 CREW
8-8.3.1 G round Tests ............................................ ..... 8.21
8-8.3.2 F ight T ests .................................................... 8-2 1
8-8.3.3
8-8.5 DOCUM ENTATION
8-9.2
SURVEY ...................................................... 8-24
8-9.2.1 Passive
................................. 8.26
8-9.2.2
8-9.2.2.1
8-9.2.3
8-9.3.1 Ranlar Rcflecriity Survey Plan
.. . ... ........ ............... 8-3
.......... ..................... 8-30
8-9.3.4 Instrumcnation and Data Analysis ... ....
. ........... .. F-30t
8-9.3.5
8-9.4.1 t.ighitn ng Protcction Survey Plan ................... ........ ..... -33
8-9.4.2 L.ightning laboratory Test .
8-9.5.2.2 Clear, D y A ir Flight Tcsis ..................................... 8-38
8-9.5.2.3 Simulated Icing Flight tIests ..................................... 8-38
8..9.5.2.4 Natural Icing Flight Tests ........... .............. ... ........ . -39
8-9.5.1 instrumentation and Data Analysis ................................
. -39
8-9.5.3.3 System Performance and
8-9.6.2 Test
8-9.6.2.1.4 Weapon Noise Measurement
8-45
8-9.7.2.1 Test Requirements ... ................... ............... ....... 8-49
9-2.2.3 Docum entation ................... ............................. 9-5
9-2.3.1.1.1 Test Procedures
Idle .........................
9-14
Acceleration
9-16
9-3.2.1.2
.................................... 9 17
Response Time ................ 9-17
X
.2
tl 'l 'li- 't lrnino ,l Ma 1mnii l'0%%..,I
w it pc.c.d
"9-32.1 2,2
1 llcIcoptkI 01 1 .111M' ,ti1 I niga-u . io t ilt>(. ............ .. .9 18
9-
IN
)-3
9 I\
.... ...... 0-
91-3
2 I 3.1 1 A niltunt I c ip ratutc 1 "NI .'. .. .. .. . . . . .1. ..... ......... .1I
9 3-2.1 1.1
,tSI ......... ......... ............... ...... Q I1Q
9-3. 1 4 otih Po c 'A biw t itl
lptatic 1 ........... . ...... 9-1,)
I CIt; t I tItI . . . . ..
. . . . . . . . .. . 9-1
9
9-3.2.1
4
,ts . . .)..............
I ... .. . . .... ()
................... ...............
9-3.3. ALCc' riC...
9-3 4 1 1,ubrication Subsyster Derionstration ............................... 9-24
9-3.4.1,1
9-25
Test .... .....-......................... ...... 9-25
9-26
9-27
...... ..... . ..............
9-3.4 2.1. Fuel
Quantity Gaging Subsystem
.. 4-28
9-28
9-3.4.2.3
Tests
........................... 9-28
9-3.4.2.3.1
.................................................. 9-29
9-3.4.2.4
9-.3.4.2.4.,3
Tests
.............................. ... 9-29
9-3.4.2.5.1
......................................
9-30
9-3
9-3.5 ROTORS AND PROPEI.LERS .....................................
9-3.5.1.2 Preliminary
I'lighi Approval
9-31
9-3.5.2.2
9-33
9-39
14-3,7.1 Propulsion Systemn Temperature Demonstration
Plan......................9-39
9-3.7.4 Documentation....................................................9-39
9-3.8 ENGINE AIR INDUCTION SYSTEM DE M ON STR AT ION ... .. .. . .. .. ..9-39
9-3-8.1 Engine Air Induction System Demonstration
Plan........................9-403
9-3.8.3 Instrumentation
94-3.8.4
Documentation.....................................................9-42
9-4
DYNAMIC INSTABILITY D EM ON ST R A TIO N ...........................9-42
9-4.1 GENERAL
AERODYNAMIC DE M O NS TR AT IO N.... . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. .9-44
9-5.1
GENERAL ..........................................................
9-44
9-5.2.1.6 of Power Available....................................9-48
9-5.3 FLYI[NO QUALITIES D EM O N ST R A T IO N ..............................9-49
9-5.3.1 Ten- Requirements..................................................9-49
9-5.3.1.1 Static Longitudinal
............... 9-50
9-5.3.1.5 Controllability....................................................9-50
9-6.2
9-6.3.1 G round Tests ..................................................
ents ................................... 9-53
9-6.3.1.2.1
9-6.3.1.5 Fault Protection and Detection .................................. 9-55
9-6.3.1.6 Electrical System Installation ...................................
9-6.3.2 F ight T ests .................................................... 9-55
9-6.4 DOCUMENTATION ............................................. 9-56
9-7.2
9-7.2.2 Production Tests ................................................ 9-56
9-7.3.1 Scale Model Antenna Test Program ................................ 9-57
9-7.3.2 Antenna Subsystem Qualification
9-7.3.5
9-7.3.7 Docum entation ............................................. ... 9-59
9-7.4.2.2 Airworthiness Qualification Ground Tests ......................... 9.60
9-7.4.2.2.1 Visual Inspection .............................................. 9-60
9-7.4.2.2.2 Cooling Tests ................................................. 9-60
9-7.4.2.2.4 Transmitter M odulation Checks ... ............................. 9-61
9-7.4.2.2.5 Operational Tests ............................................. 9-6i
9-7.4.3.1 V
9-61
9-7.4.3.3
Sys tem s........................ 9-64
9-7.5.3 Navigation Subsystem Flight Tests .................................. 9-65
9-7.5.3.1 Air-worthiness
9-7.5.3.1.1 Test Requirements ............ _............ ................... 9-65
_...................9.65
9-7,5.3.1.1.4 Vibration Tests....................................... ..... 9-66
9-7,6 ELECTROMAGNETIC
9.8.1 GENERAL
9-8.2,1.3 Coniemnination Protection .................................. 9-68
Pressure............................
9-70
........
............ 9-70
xv
9-8.2.2.3.2
...................... 9-72
9-8.3 1.1 High-pressure
9-9.5.2
L ......................................................
9-80
9-10.2
PERSONNEL
...................
9-83
9-10.3.6
9-11.6.1
9-89
9-12.1 G EN R
9-12.2.2.1 Helicopter Performance Tests ..................................
9-12.3.1
9-95
9-12.3,1.2.5
9-12.3.1.3.1 N onfiring
9-12.3.1.3.2
Firing
9-12.3.1.3.2.4 Handling Q ualities ............................................
9-12.3.1.3.2 7 Engine
Perform ance ........................................ .. 9-98
9-98
.............. 9-98
9-13.2 SEPARATION
CHARACTERISTICS ................................ 9-99
........................................
10-1.1.3 Model Construction and
Yesting ................... 10-5
10-2.1
10-2.2
10-2.2.6 Category
10-2-2.6.3
Contract
Compliance
De1inonstratioji..................................10-8
10-2.3.1 Transportability
TEST
R E Q U IR E M E N T S.. . .. . .. . .. . .. . .. . .. . .. . .. . .. . .. . ..11-2
11-1.2.1 Contractor's Development and Airworthiness Qualification Tests... . . . . . . . . .11-2
11-1.2.2 Army
11-1.2.4
11-3.1 GENERAL..........................................................11-4
11-3.2.3.1.3 Documentation ............ ................. .......... ......... 11-7
11-3.2.3.2.1 Test Requirements.............................................
11-9
11-10
11-10
11-12
11-3.2.3.4.3
11-13
11-13
11-14
11-3.2.3.5.3
11-15
11-16
11-17
11-17
11-19
11-5 D O CU M EN TA TI G N .................................................
11-21
GLOSSARY
Development ....................
3-2
Tests for
Adhesives ... 6-10
6-2 Master
Tooling Coordination .........................................
8-5 Pressure
D;stontion Plot .............................................
............... 8-32
8-11
8-54
Survey ........................
8-57
9-1 Attitude of Skid Gear for Drop Conditions II III
.................... 9-7
9-3
H istory Recordings) ................................................
Chart ....................................
9-37
...............
2-2 SUMMARY OF CTP TEST REQUIREMENTS-ALLIED EQUIPMENT 2 2
3-1 HAZARD SEVERITY FOR HELICOPTERS ..........................
3-7
3-2
3-4 POLE ........................................... 3-9
NO. 151 ...........
6-3 TEST METHODS FOR CCRE MATERIALS
AND SANDWICH STRUC-
T R ES .. ....................................... .... ............
FEDERAL TEST
N O . 14 1 . .... . ...... ........ ... ... ... .. ... .. ... ... ....... . . 6 -11
6-6 SELECTED TEST METHODS OF
FEDERAL TEST METHOD STANDARD
6-8 STEEL FORGING TEST REQUIREMENTS BY GRADE ............... 6-15
6-9 REPRESENTATIVE HEAT TREAT
7-2 EXAMPLE FUNCTIONAL TESTS ........................... -----. 7-5
7-3 ARMOR MATERIAL SPECIFICATION ............................. 7-7
8-1 TYPICAL HELICOPTER MANEUVER SPECTRUM .................. 8-3
8-2
8-5 LIGHTNING CURRENT COMPONENTS AND EFFECTS ............. 8-35
8-6 ICING
9-1
xxiii
AMCP
706-203
FOREWORD
The Helicopter I.rgifferitig Handbook forms a part of the Fngineeiing Design
Handbook Series which presents
Army
equipment.
706-201,
Detail Design, this part is inten-
ded to set forth explicit design standards
for Army helicopters, to establish
qualification requirements, and to provide teclical
guidance to
the Army.
The first volume of the handbook. AMCP 706-201, discusses the characteristics
and subsystcns which must
Aditionally. possible design problems encountered during helicopter
design are
of the vehicle from an approved
preliminary design configuration. As a result of this phase, the design must provide
sufficient detail to permit construction and qualification
of the helicopter in
pliance with the approved detail specification and other requirements. Design
requirements for all vehicle subsystems also
are included in AMCP
is divided into
II chapters, and
1, the introduction
thice-part engineci
fEnginvering in the Frngineeri ng Design
Handbook series. It wsF prepared by Forge Aerospace, Inc., Washington, D)C., under
subcontract to the Engineering
The Engineering D~esign Handbooks fall into two basic
calegoiies, those approved for
for security
reasons. The
Engineering
activities and
It will he noted
acquiring these
Hiandbooks Iollow.
having need for
Commanding Officer
"Need -to-Know'
Flight Standards and Qualification Division (AMSAV-EFI). with their
recommendations
include
recommended
mended Changes
to Publications
atnd will
PreliminaryDesigi, is the first
volume of the llelicopter ment are not discussed. Governmental responsibilities
tHandbook Series and discusses the preliminary design are always related to only the procuring activity.
phase and contract definition procedures, including
the Although dependent ultimately
reliability, and maintainability considerations. At the which begins with the initiation of
system development.
conclusion of the preliminary definition period, a heli- Included are
design reviews, duringboth the initial sub-
copter
configuration will have been selected and its system definition phase and the final detail design of
general characteristics and capabilities defined in pro- assemblies and installations. The construction and in-
curement specifications.
special-
definition, in response t) a Request for Proposal (RFP) ized design review. Conducted as
ei ly in the
pessible, the mock-up review
pe; ,nits evaluation of
interaction between all required
greater detail throughout
A MCP 700-202,
tuil Design, the second
volume, describes the follow- to the availability of components or complete systems
on detail (or engineering development)
phase in terms for test, analyses are performed to substantiate subsys-
of design requirements, criteria, and procedures for the tem configurations and performance. Also during this
total
period
detailed
plans are prepared for the testing of
systems are re-examined, refined, and defined as the components, subsystems, and the
complete helicopter
as required to verify compliance with applicab e design
cation
requirements. The preparation of
these analyses and plans
and their
gations, analyses, and exploratory testing. Detail review and approval by the procuring activity are
sig-
This volume, AMCP
706-203, includes the require- gram.
ments and procedures for substantiation of the airwor- Qualification of a new model helicopter includes
thiness of the vehicle through proof of compliance with qualification of components, of subsystems, :0nd finally
contractual design requirements and performanceguar- of the complete helicopter system. Each of these efforts
antees.
Airworthiness, as defined in AMCR 70-33, it,
"a is a discussion of Governmental testing,
which
sub-
system or component to function satisfactorily when with contract requirements. This testing includes that
used within the
It
is
the intent of this volume to delineate the iespon- helicopter operation for
follow-on Governmental test-
sibilities of both the procuring activity and the contrac- ing and for the
preparation of operational and
qualification program for a new
model helicopter. The helicopter qualification and preparation
by
the procur-
helicopter systems
to which such a program is applica- ing activity of the Airwoithiness Qualification Substan-
ble may be completely new, or may be the result of tiation Report, Governmental testing continues, in the
major modification of a previously qualified system. form of Service Tests, to insure operational suitability
f-1
determie to what degree the helicopter meets programs may vary
from
the characteristics stated in
the requirement document. in this volume, the procuring activity will specify in its
However,
Proposal the extent to which these require-
ness qualification is
ments
are
book. helicopter. Deviations from this
handbook not specifi-
in the RFP will be considered when
tion requirements have been identified with the
con- adequately substantiated in the contractor's response to
language makes use of the imperative the RFP.
This handbook will not be incorporated
in a
document in contract by
However, the
planning of a qualification program, the word handbook may be
furnished to contractors as abasis for
"shall" has been italicized in the
statement of each such
requirement. Airworthiness
1-2
i4
of-Flight Releases and/or Interim Statements of Air-
The Coordinated Test Program (CTP) is the pri- worthiness Qualification required during enginLering
mary development
planning document used to des- development. It also permits the issuance of a
State-
ing. The CTP
of an Airworthiness
completion of the
AQS
is prepared
by the Army Project Manager, and has tions, and procedures specified in
the following objectives:
1.To
serve
and
among
the
agencies
which
require
3. AMCR
70-33, Airworthine,.;
The types of tests which comprise the CTP, as well
types to be used during testing. as the test
agency,
test
are
The CTP also must provide
the justification for corn- summarized in Tables 2-I and 2-2. These tests normally
bining tests, for conducting them concurrently, or for should be conducted
in the sequence shown in the ta-
eliminating them
bles, especially where test results are required prior to
unnecessary
testing.
further
testingand
un- climatic conditions
will be encountered.
that and integrated
all elements in this by fund and time limitations.
analytical process is the Airworthiness
Qualification
described fully
Proposal 2-2 AIRWORTHINESS
formal (AQS)
tractor demonstrations, and
plementing
the procurement of any major Army air As noted in the previous paragraph, the contractor's
item
informa- airworthiness
tion then
helicopters.
die contractor. Inherent in the AQS is the dissemina- For each
helicopter system subject to qualification or
tion of data nect.ssary tc demonstrate proof of compli- requalification because of' major modifications, a
ance
detail specification. qualification specification will be prepared to establish
2-1
2-2.2 AIRWORTHINESS QUALIFICATION
work is divided into those tsts to he per-formed under
an
propriate procurement action such as a product im- The Airworthiness Qualiticatioii
Spccifcatioi %kill
provemnent contract.
HARDWARE 7ESI ODIECTIVE
QUALIFICATION SUBSTYSTEMS
-T STSAQT I
RELIMINARY CONTRA-CT__
OFCORRECTIONS
MTERIL
ACHIEVEMENt(
OF
APPLICAEILE
MILITARY
SUMMARYF F I I E N C E S REVEMEDTS-.-AI.PRIESJLTS.
E
IDPNE
TESTCPIATO
OFSJTCTIVDEGREE
LATHIOR
O
DEORTIOTET SPECIFICAELOMINTNS
QITRAI N
ETY-FEETRMNAIO OFTTS 1jLTVSRIAIU1
MAINRAINATILIFTY. ENRE
ND siIRAFE
C .HA1 T E I S T S T T N -LPEN N IWRHN
DEITESTS ELETREITEM. AND HTSNTAN P ACKARTES U~IITIN-
S'
DEONRATION SPECIFMICATIONSFLIH
SE (ICOTST DETERMIINATION OF
DEEOMN2ONRC AEBEN2VLE
of helicopter. are
delineated
2 Design Review and
3. Mock-ups
design pit-
4 Procurement
, Forma)
These
elements
are
described
of all
2-2.2.3 Mock-ups
which
the results of the
System Safety Program (SSP) are to The specifications for the mo.k-upt; required by the
be applied in the airworthine;s
qualification of
for
a
tem. The provisions and requirements of the System dctailed "Jrcussionof mock-ups.
Safety Program
as- 2-2.2.4 Procurement and
tion or
system. The contractor
will include two areas which In order for the procuring activity to maintain cogni-
ultimately combine to form the basis for the Systen
zance over the detail configurations for which
airwor-
is
desired,
of
procurement
tion
in- specificaxions of contractor-furnished equipment
sure that all components
tests, system surveyw, and (CFE) components are essenlial. To insure adequate
are planned and conducted in structural
integi,,y, material and
close oordination with the
System Safety Program. also must be subjected to the approval of the procuring
Hazard analysis will be an integral
and essential
factor activity.
list those procure-
which must he sub-
Drawings
because 3. Interface control
sible to try to standardize these areas.
Participation in 5. Installation
the design reviews does not limit or restrict other elc- 6. Control
ments of the procuring activity from the responsibility
of insuring
contractor procurement
in the
review of detailed drawings is required for AQS. Details of
procurement and process specification
each subsystem.
Basic reasons for the inclusion of these requirements are described in Chapter 6.
2-3
by the
procuring activity.
adequate integrity
As a
minimum, formal
military qualification
tests of
for use
components and subsystems
complete
"'must-pass'
tests.
The
primary
objective
design defi- 5.
Tail rotor gearboxes
to reline the component or subsystem design. The S. Fuel
systems
by adisassembly
accomplished in, he presence of
representatives of the
de- contractor,
the procuring
tected any
applicable.
The
determine if the components
the AQS.
phases. The first in-
of all parts immediately
s4mhly;
the
available to
the inspection
include, hut not be limited to: (1)
visual, (2) di-
ground test vehicles
ultrasonic.
will
be
is
for later utilization in the
completed
satisfactorily
bWfor,
Components
Additional
bench
is given in Chapter 7.
2-4
,to
survey should
System surveys include all tests designed to deter- environmental requirements under all specified operat-
mine system characteristics and demonstrate sntisfac- ing conditions and modes (see par. 88).
tory system operation within the normal flight en- 8. Infrared (IR) Radiation
and Countermeasure
IR
radiation and countermeasure
airframe unit design requirements. In determining sys- system survey should be performed,
if
signature has
operating
environments. The requirements of par. 2- tion of all trade-offs made
in minimizing the signature
A
I, F ight
estimate of fatigue lives and determine 10. Lightning Protection Survey.
A survey will he
if resonant
frequencies of critical components are tuned performed to esiablish a high degree of confidence that
to the frequencies of the primary exciting forces
(see the helicopter
system can survive a lightning strike. As
par. 8-2). a minimum, the survey will demonstrate that the fuel
2. Engine Vibratory
vibratory
3. Propulsion
exchangers, etc., do not exceed their allow- 2-2.2,7 Formal Contractor Demonstrations
able temperature limits (see par. 8-4).
4. Engine Air Induction
Army require-
of the helicopter
gine exhaust subsystem surveys will be conducted to
evaluate
operation
and
performance
(pressure
survey)
tions
is:
titative
data
should
be
collected
during
unaccelerated
design
requirement.
tile flight 3.To obtain quantitative information on safe flight
envelope and of allowable
speeds (see par. 8-7). limits for operation by Army pilots
2-5
JII
delivery to the
3. Lubrication
Subsystem D)emonstranton.
A lu-
brication subsystem
demonstration is
Demonstrations
systcm(s)
oil
discharge
demonstrations
should
system
adequacy.
2-2.27.4
Helicopter
treme temperature
Demonstration
requirements
specifications
(see
of
the
9. ElectromagneticCompatibility(EMC)Demon-
helicopters. Therefore,
this test
phase normally
will continue past the publication of the Airworthiness
tromagnetic environment that can
operation
will demonstrate
that no single subsystem operates as In the preparation of the AQS, the contractor should
a possible source of electromagnetic energy that can propose a schedle which
will result in a logical se-
cause other onboard equipment to malfunction
(see quence of the required analysis and test efforts in order
par. 9-7.6).
be qualified
the helicopter be carefully tested
on
the
each of the et phases
be demonstrated
stisfactorily on
the ground
analyses to amsure that
be adequate to determine
program.
in accordance
with the
A
sepa- the ground
flight of the
using either
a tied-
envelopes will
a minimum
static test
gear drop testing
This handbook does not attempt to regulate the se- which, as a minimum,
will have demonstrated
tests essential to air- landing
at design limit
worthiness qualification
of a
new model helicopter. The ficieni component fatigue test data should be
scheduling of these activities
is largely a function
compo-
initial flignt testing (minimum
assumed loadings).
system should have completed a
ing
AMCP
706-203
of this testing must have been at maximum rated torque 5. To brief each witness/observer on the status of
and speed, but pertinent transient condition., also the test, including
preceding and
subsequent itsts. The
should hae been tested reasons for past failures and retesting requirements
Demonstration requirements
with other
tems,
as defined by pertinent Military Specifications, in equipment tests also should be described.
several cases include the stipulation
that
an analysis of 6. To forward corr.pleted witness reports and
com-
system capability performance be submitted ments to the procuring activity. fe will take further
approval, together with appropriate subsystem draw- action on reports ard provide
additional
required.
apparently a sequence
requirement, such stipulations 7. To insure that the witness signs off tht- contrac-
normally will not affect qualification scheduler the
analyses
required
are
performed
routinety
theiefore, be completed
well in advance of subsystem testing.
test(s) to be conducted, recent
changes
in the test plans
The RFP for aspecific model helicopter will indicate (if any), an orientation oni the facilities to be
used, and
the number of helicopters to be assigned to test and
pertinent safety considerations including special
equip-
clothing to be
any neces:,ary restrictions.
qualities and performance, avionic,, and armament- 8.To perform as the test witness when an author-
the contractor will
witness hws not been appointed or is absent.
helicopter the proposed schedule. lI addition to
iiiinun risk to the qualification program,
ovcrall 2-2.4.2 Test Witnes$s
reviewing
a test(s) contract reqibireinemWt (system spcciications.
proposal.
the test(s) to
2-2.4
TEST
COORDINATION
sentative,
he
is
responsible
A test coordination
executed
by
the
procuring
documentation and data (e.g., plans,
nation will be provided by the procu|ring reports,
drawings) which he will use hi~s witnessing
Proposed operati.g procedures fc-
which follow. 2.
Specia' briefings unique
to
witness.
Coordinator The test witness will review and countersign the test
The duties and responsibilities
of the test coordinator
are:
verification of the scope and details of the test, and that
1.
him
fr rapid and timely any requirements
for special witnessing reports.
or
as required.
data and information, such as plant procedures, de. To insure - effective test witnessing program, the
tailed test procedures, and forms
on which
in
2-8
2-2.5 AIRWORTHINESS
in sufficient time in order that he or
his representative may witness the test tn cer- An AQSR will he prepared and published bv the
tify and approve
the
obtained during the test. If the test is such airworthiness qualification program. This report will
that interpretation of the behavior of the arti- contain, hut not be limited to. the following:
tc under test
2-2.4.3
Cognizant
Service
Plant
Activity
of ce'npliance with
the CSPA to assemhle engineering talent equal specification design criteria
which may be included
in
4. A description of the operating instructions
and
manuals.
Tech-
nical justification for all such instructions
that a qualified Army witness, generally from outside
will be included.
a signifi- 5. Ancin all dat
usA inqaificationap
the test wit-
by the procuring
drawings, and Governmental
will
furnish
An adequate file
test wit ness(es) voices about
the test setup
and/or pro- activity
qualification pro-
test wit- gram. Copies of pertinent documents
will be
witness
and
test coordinator is
is obtained by insuring that:
System safety is defined as
"the optimum degree of 1. afe features consistent with mission require.
hazard elimination and/or control within the
con- ments are designed into the system from
the beginning
operational effectiveness, time, and cost at- of the design process
tained through the specific application of management,
scientific,
and
engineering
principles
throughout
all
2.
Hazards..4;ociated
with
de- 3. Control is hazards that
sign and analysis, management, and supervisory con- be eliminated by design selection to
protect personnel,
the accomplishment
of system safety
management, re- 4. Minimum risk is involved in the acceptance and
search, and engineering tasks,
and is an essential ele- use of new materials and new production and testing
ment of the airworthiness qualification of the system techniques
The normal helicopter engineering process is illusq
trated
pbases of
a system
882 are shown in Fig. 3-1 opposite the equivalent tasks 6.
Retrofit actions taken to improve
performance,
are only considered typical atid not
necessarily com- sidered from the standpoint of safety with respect to
plete in number.) The system activity starts early in
the interfacing subsystems
or allied equipment
and
con-
tinues throughout the entire The progranis and operational experience used
process described subsequently
is applied in
of previously
S) .tem safety requirements
tvK, nand-
book. Only
through the airworthiness qualification are
included.
The
qualification
programs. shows a logical approach to attaining the system safety
objectives specified in par. 3-1.1 The process is re-
3-1.1
OB.EC
fIVES
peated
system until the requi-
operational mission The SSPP
effectiveness
through
the
PRE ININARY mAZAHL
ANA LYS S
2I
AMCP
706-203
3-1 2.i Known Precedent (Block A, Fig. ard', accorling t criteria specified by
the.
procuring
3-k)
activity
degree of severty. Evaluation
of identified hazards re-
effec-
he hased onl the exprience and knowledge gained from tiveness, system
performance, and program :,ucccs,.
which This categorizalion and
process asto appropriate correc-
n;'it::rcl or injur:c, ordeath
to personnel. Those design
fuiture
,, Ith altbets safe operatinn.
1 hr
boundaries of
and it, onstittetnt elements
.o
lf'L: cycle Such delineation establishes
the limits for managemrent is presented with a tool by which deci-
sticed ig steps
sions can LC made in the light of other program
con-
the arnaly.:i,
necessarily will result
ni.,hodiral rnarner. Peginning with
preliminary haz- in the modification of some eletent or .elementsof the
ard analyes of desi n concepts and continuing through helicopter
systtm. As a result, the delineation
of the
system s.fety process thcn is ,epeated as
requirea until
steCh time as no unacceptable additional hazards
are
cotvractor
This step insures
for hazard analysis best suited for the particuar system th;t
a new flazard is not inadvertently
introduced into
system while another hazard is eliminated.
level of detail in
to
as a result of the
p,ientially may cause damage, loss, or injury. Such .-ystem safety process ,re evaluated for
their
effective-
calling attention to undesirable
features wlhich either satisfactory evaluation results in increased assurance in
,:at be eliminated or controlled efficiently earl) in the the level ,f safety of
the system
of course,
hazards ident'fied
of
of the hazard. Categorization of haz- sten in the process.
I 3-4
Analytical techniques alone will not he sufficient to
adequately
identify
engineerinp
betwveen subsys-
K) terns
T'he assu
interrelationships which could lead
being met is cumulatively inc Ised as the program are
he height
of the
p)rogresNses and contributes
incr as%,d knowledge for the location of the pilot relative to the rotor path.
subseqluent cycles of
system
safety
analyst
3-1.2.12
Airworthiness
Q9ialificaion
for- helicopters.
And the
Ultiatey, hesse
saety ces *, in ata ditions invoiving only' haidwarc. ih,2 interactions of
Ultmael,e ymm sfey ;) )cssresults
and
between
airworthi ness qualification. Methods
potentiafly
be
Qualifi- hazardous conditions
classify
cot-sequence of the
these analyses form a must be considrred before the procuring
activity can
mneasure the effec- ards. The
contractor Thall deveop a procedure to
tive
There
are
several types of widely used analyses for gram requiremems. One
possible range of valnes for
the
*
upon
how the four hazard levels
the. level or detail required by program
phases, require-
tor
mcrnts for quantitative or qoralitatiye results, and the the helicopter of interest. lIn this cast, Pach hazard
level
in term-, osfsystem objectives, functional
3-5
AMCP 706-203
capability, and personnel safety. All possible hazards in significance and the resolution of the hazard
is
deter-
severity against these mined, there is need for assurance
that proper
letters in Table 3-I tive action has
been taken. This can be accomplished by
assigned to each hazard.
Table 3-2 provides a range
of probabilities, for any A particular
type of design review which is effective
given hazard occurrence. The same code letter proce- for
system
safety
is
5- 3 .
Table 3-3 involves an intermediate conversion of method of identifying additional
potential hazards. Ad-
ditionally, the mock-up brings the
subsystems together
into a dollar equivalence before a code letter can be at an early stage, before interface problems become too
selected. j expensive to change
Once three code letters have been assigned to each
possible hazard, they are combined to form one index
of significance.
The Hazard
Totem Pole
of Table
in order of PLAN (SSPP)
importance or significance.
MIL-STD-882 discusses the inethods of resolving
Safety Program is the System Safety Program
Plan
This plan shal constitute a detailed
description
hazads.Thefirt,
contractor's approach
eliminate
an
identified
hazard
by
selection
of
a
design
lates
is to make the system tolerant of the hazard.
The purpose of the SSPP is to provide a basis of
understanding between the contractor and the procur-
hazards are stipulated in MIL-STD-882 in adescend- ing activity as to how the system safety program will
ing order of desirability. The first
alternative is to be incorporated into the development effort, It must
reduce
of
a hazard through the use of contain the necessary details for determining adequacy
appropriate safety
and measurability; adefinition of the safety effort to be
not require human interventionbut
the management structure through
matically if the specified
will
The
next
choice
is
to place warning devices in the of the milestones by
which it can be monitored. The
system
to
make
known
to
the
crew
the
existence
anthsfeydarpoigssemPstciet
reupect
biut there imdito e mmonlube in h experience serves as an important safety design consid-
respect,
but
be
design. Such features must be coordinated closely with face
between contractors and subcontractors, including
the
The final, and least
disseminate, and enforce special operating procedures
Only the requirements
regarding
needed to support the system acquisition program from
these procedures are a
through completion of airworthi-
of the inability
to verify corn- ness qualification are included in the paragraphs which
munication
of
the
must follow.
3-2.2 SAFETY
tion techniques which may be used, depending on the
--6
• -... . ,g,:W-W
package
Airworthiness
(b~e
discussed
in
the
disciplines. The
si
complexity
of the systemn and the requirements of the HaZard analysi: is a qualitative inchniclut used
AQP. A necessary criterion
for
depth and adequacy of primarily to assecss the ope-ational sa~ylevel of the
the technique employed is traceability,
i.e., cause to
CODE DESCRIPTICN OF SITUAT'iON
CUMULATIVE HOURS
OF OPERATION
CUMULATIVE
CUMULATIVE
CUMULATIVE
CODE
CALCULATED
DOLLAR
EQUIVALENCE*
OF POL-
THOL THE HAZARD OF INTERE3T.
3-8
ysis is primarily quantitative and uiijliics detailed corn-
The hazard antalysis is based on an operational se- ponctnt failure probabilities to calculate
overalil probs-
(Refs, 1, 2, and 3).
their interrelationship. shown- This analysis
also can However, it also can he usedqiualitaivcls. to identify
the
safety
probabiliiies. io
the safety
COECOMBlNATlIt,2
trece,
event(, 'Ahich contribute to the
HAZARD ~ - ~ ~NUMBER
Each
event
that
SIGNIFICANCE c, crF0 HELICOPTER imay cause such at ondition isassigned'to a failure rate
RANKING
1
> HAZARDS
of the time
in a
a constant value
2A
example, anl engine is
input eveno, must
event
64
M
Analysis
(FMHEA)
and testing
thehamrd ote4 cdes~oreah o th 2 a~rd araetes, phase,, which assures a high level
of'saferty before
code combinations, i.e.,
in this initiation
is he most signifi-
cant and code COfribinatio DM5Is least signijficant Lcoeticopter
which have a serious
of mission anid on
criteria
att three aalssosi t
of the effets
and prefereheent c odes should bc cfinsihed prior to prcparlng a of these failures tin the mission capability of the systemn.
hazard totem pole.
block dia-
2 The codes heing combined are tbo sc front I able%
3-1, 3-2, Pnd giant showing
the critical funictions which conistitute
33
(the system. A "critical function" is one that musit be
3-9
AMCP
706-203
performed if the system is to operate. In this diagram, 2. The testin,3 will bt carried
out in a safe manner.
the blocks are
All additional
function procedures, instrumentation, iest hardwae, tc_ are
A failure is now defined as
a break in an output
line propere intruentatinmte
alone or in critical combination
with other failures, all
ability based upon
can Safety data requireine ts during the development
this assumed functional failure actually occfir, i.e.,
phase
what piece
of hardware would have to fail first to of the system life
cycle and specified in the Contract
result in this functional faiure? It
is not necessary for
the ana yst to identify all possible hardware failures; if
safety data acquisition and acceptance
will be
in ac-
he can establish some cordance with MI.-STD-882.
probability of system failure. Secondly, how can this
failure mode be removed, i.e., must this be
designed this
REFERENCES
way? I. J. Feutz and J. Tracy, Fault Tree for Safety,
1)6-5713, The Boeing
Co. January 1966.
of Fault Tree
Analysiu to Dynamic Systems,
Safety tests shall be integrated into appropriate test The Boeing Co., presented at the Sy,.tem
plans. Partial verificaton of safety characteristics
or Safety Symposium,
procedures
may be demonstrated by aboratory tests, 3. J. B. Peller, Fault Tree
Analysis as a Towfor
functional mock-ups, or model simulation, when ap- Sy.item Safety Engineering,
Report
proved by the procuring activity. The detailed test X5. 1002/319, North American Aviation/
plans
that: Autonetics,
Anaheim, California,
4-1 INTRODUCTION
ton
posite list of data
which could be made available to the will bv thse issues in effect at the time of formal solici..
Government
& proposals.
for
a
specific program should be tailored within this The contractor will
use the specifications and stand.
list. Subsequent
ards in the order of precedence established by
MIL-
required
content of specific of data. SrD-143. This Standrard prescribes the criteria
which
DD Form 1423 is the only
contractual instrument govern and control the selection of material and parts
for the purchase
of'data and documentation.
list, TD-3,
and phlet
No. 70-1,
may be informative
only, .or for review, approval, or a degradation of performance of the total system. In
other
action.
or stand-
priate sections of MIL.-D-1000 will apply. The DOD ard, or a manufacturer's specification, is required. If, in
Index
of Data Item Descriptions,TD-3, provides usage the opinion of the contractor, the optimum specifica..
guidelines and
tion or standard for a specific application
is rot listed,
should be submitted
Form
approval, before use.
Justification
during the
and
contemplated
provided at strategic milestones during the qualifica- in order to avoid
potential delays in ihe qualification
tion program,
of the procuring aj'tivity. An "audit trail" is established Conitractor documents shall not be changed without
s&,
may be
documents is given on
responsibility to re-
tivity to assess achievement of design requirements and quest and obtain approval for continued usr,of such
to determine
problem areas
A
design
review
of
detail
drawings
for
each
subsys-
tem
design criteria
Data and documentation shall be submitted in ac- 2. Insure that there are no obvious design deficien-
cordance
with
the
system safety, maintainabil-
which is being recommended
for analysis and te:t
6.
shallprepare, assemble,
and provide
7. Weight Balane Control and Management
uled in the AQS.
The packages will define
include an agenda
safety, reliability, and main-
4-5 DESIGN
throughout the
and
result
design information must be furnished for simula-
-hallbe provided. Also, the
the construction tcstiig
fice facilities, and administrative assistance to facilitate will be kept current by prompt submittal of pertinent
conduct of the Mock-up Review.
Mock-up data
and reports
which include:
inspection checkoff
lists shall
be provided,
suits, and any conclusion,
and the
is
made
Aerodynamic
INVESTIGATION
PROGRAM
to axes consistent
flying qual-
and schedule
purpose and
ity report
models to 3.
the ranges
of test
submitted.
tunnel flutter
gations. (if required) flutter and divergence analysis reports
will
reports will be prepared in accord-
contractor will make preliminary contact with the ance with MIL-A-8870 and will compare the flutter
facility to determine feasibility -nd desirability
of
con-
blades and for
obtain ten- the
the tests are to be with
the requirements of
activity, freedom from flutter
no
flutter
progrars wil
be made
to the
out the
response
characteristics
test facilities simulated analytically on digital and/or analog con-
to be
construction. puters, a report will he submitted outlining the pro-
Model drawings
4-3
of
4-7.2.2
Flight
Simulator
Program
Report
controls,
aerodynamic
o- boosted
Basic Aerodynamic Data
An initial report containing complete information on The contractor will submit
all basic aerodynamic
the aerodynamic stability
report should
tc reflect helicopter configuration, and the documents and/or
the development progress of the helicopter design, par- references
showing ihe derivation of these data (draw-
ticularly the latest and most applicable results of the ings, analyses, substantiating
calculations, tests).
If the
any major configuration changes.
in
con-
tain
all the data necessary to define the aerodynamic figuration, Reynolds number, surface conditions, and
configuratici and its control system characteristics, regimes must be explained. Revision pages will be sub-
together with relevant
reflect significant changes. The types of data
weight, and moment and product of inertia. In a sepa-
which
data neces- 1. Drag
c-,atrol characteristics
wing,
stabilizing
throughout
as
ternal
stores,
thi; conversion
should be
illustrated. Where
appropriate wheel heights.
A complete description
and fuel
in accordance
with MIL-
surfaces,
system,
noz-
drag,
bleeds,
accessory
and balance status
in AN 01-1-40
ratio, twist, taper,
and tip geome-
.ry, and hovering tip speed; wing and control surface 6. Actual weight reports and appendices. Pnor
to
components and the
helicopter; overlap and
projected disk area
for tandems. vice Plant Activity (CSPA) will insure that it has been
weighed to determine
4-7.3.2
Substantiation
from astrength
or flying
quality standpoint,
Characteristics
demonstrations
tedw e a n
not later than six
(SAC)
Charts
philosophy,
the
procedures
group
Chart
will
required in par. 4-7.3.1 and as accepted by the procur-
teed
and Management
DATA
weight
schedule.
H-46855,
and
the
appendix
appear in
nunbers,. le ttcrig.
pars. 4-7.9.3 to 4-7.).7 will show the major
3. Operator ta laansiion planstructural
design features including
all important fit-
other discon-
6. Internal and external noise survey data tinuities, typical sections through
load-carrying
iner-
4-7.7
SYSTEM
SAFETY
DATA
quested
deviations
from
detail
or
other
applicable
de-
The data
to be
not be delayed until
and copeeflw-nasmyitlainren-
each contract end-item
been prepared (par.
DATA
and 10-2.1). (See par. These drawings, ccnsisting of side elevation
and plan
4-7,13(17) for reliability test plans and reports.) views, and including the necessary cross sections,
2. Maintenance engineering
analyses, in accord-
ance with TM 38-703-3 (par.
10-2.1.3).
structure will be in dashed lines and the system installa-
tions in full lines.
The information shown must be in
4-7.9 SU8SYSTEM DESIGN APPROVAL agreement with the weight and balance data required
DATA
an d
and 4-7.9.3 Rotor(s)
drive systems and equipment subsystems-will be sub-
mitted to the procuring activity for review during the Drawings of non-UiFE rotor(s) and
propeller(s)
will
be the
or first drawings
of the main structural
which show the required information. Legibility of the material together with typical cross sections in the
drawings must be. such that
all
4-6
n.et,,; calculatioi~s
and cal-
bulkhead
loc:atons
against
urisetting
These crawings
wil. nclude
'ncluding lohoded
and unfliN-ded
ot
memhlers;
anism
of n ;cale
in which
outli-ted
it, thle wing.
4-7.9.6
These drawinigs Will inLlude - llaii and elevation quired in Appendix
A of this chaptcr-pars. 2, 3. 7. 9a,
view of
the fuselage structure s-howing centerlines
of all 8d, 9b, 9c, IlOd, and I Ok-must be shown,
as applicable.
structural
main an(:
auxili-
material with typical cross sections of stringers, bulk- azry gear showing principal membe.-s.
it the gear is
be T-hown in the fully extended arnd
masts, stabilizing
and the most critical clearance di
miount, and jacking ano/or hoisting sling attachment mnensions of he wheei well
between st uct ur-i 1memibers
fittings and carry-through structures,
and installation and other e~quipmetit will he identified. The principal
and assembly of fixed and isiovable sectins of
cockpit
anid emer- shutt dra; brace,
ttnsion strut, torque
armns,
jack-
gency controls. The drawings must be in sufficie,:t dc., points. towing arnd tiedcwrn
fittings, wheci
s (iAnd
employed it: cis if used), retr,sc_,ion Land extension linkages, aclua-
reinforcing and
iikagcs, steei)E. and/or
hinges, tracks, rollers, guides, lift assemblies, and other uplocks, and downlocks. Wheel and tire toe-in and/or
components of movable section mechanisms; the "amber aingles
in
relationi
Oulline of door linkages will be shown in
and intermediate positions; and the method of emer- relation t:) gear
linkages
information should be
should be accorr- listed or indicated for all principal members
of the gear.
steering, towing,
and turnover angle draw-
required for both normal and emergency actuation tun- ing, consisting of a plat, vinw showing the tread
and
4-7
max- those specified for the hull
(par. 4-7.9.7).
imum auxiliary Fear swivel angle for towing using tow-
ha; and minimum turning radius about the main gear; 4 7.9.11 Landing Gear (Ski-type and
Bear
and turnover angle with the most critical CO location. Paws)
4. Tiedown arrangement drawing,
consisting of a Drawings,
'i.m
control
drawings.
attachments
to
helicopter
gear;
fuselage,
wing,
ind
tail
similar
.t4
fittings; and angles e.terdingto ground tiedwn points, components of the ski gear
configuration, wil
be sub-
mitted.
t
ig
all
fuselage
strut points.
AMCP
706-202.
1.
Propulsion
system
schematic
drawipgs
showing
arrangement of the location and iientifica-
trol urawirigs, as applicable, for the: tion of all pertinent components of the systems and
a. Nose or tail wheel
elements: hlbrication, fuel, air ind'iction, cooling,
b. Nose or tail wheel
tire power transmission, auxiliary power, engine
inlet anti-
Nose shock strut icing filtering or particle sepaator, accessory drives,
d. Nose gear steering and shimmy damper firewalls,
infrared radiation
bumper wheel trols, and smoke
abatement. For turbine engines, in
f. Buniper wheel tire accordance with MIL-D-17984. a reporl of he calcula-
g.
Main
whcti
assembly tion of duct losses will be submited with the
induction
i.
exhzust
pressure de.ign limits
for
1. ki installations
will
location,
eletrwents: engine,
plant, fuel, lubrication, air
starting, propulsion controls, engine ialet
anti-
cation control drawings simila: to
those cited in par. icing, iltering or particle separator, accessory drives,
4-7.9.8 and as applicable to components of he skid
gear infrared radiation suppression, power transmission,
configuration, including ground
tems,
;nicluding
aft,
complete list of all contractor-
lateral CO ocations. Water clearance of critical heli. furnished components used in each applicable system
copter structure, stores, and propeller
to
This list need not include fuel and
oil
will
2. Float
line drawings
4-7.9.7). follows. 4L chemnaric diagram will be submitted
for
4-8
approval, rfpre-
sei.tatives
component as either "surveillance"
changes subse-
and/or deve.3pmental
(other modified or off-the-shelf
which will be
activity
changes have been
sheet will
measured vdl-
ues.
in accurciance
to allow
as
category, the procuring activity's decision
will be final.
tion of any
4. Design data end
will be included with
tanks,
and
a
com-
plete list of all piping and fittings
(including tank fi-
both elementary, single-line
lubricating oil systems.
Nonstandard
of instal-
5,/A complete
formance and functional
sure,
equipment installation
jor items of
deviations
data,
MIL-L-6730 must be
dicated.
lions and substantiating
data in accordance
arce
with
MIL-E-7016.
Letters
of
transmittal
will
com-
the power supply. These 4-7.9.16 Avionics
analyses
are:
will form Contractors
General arrangement drawings of avionic
4-9
,n
all ma- 4-7.9.18 Crew Stations, Furnishings, and
jor items of electronic equipment, the exterior arrange- Equipment
ment of electronic controls for crew members
including
mount
clearly
panels troops,
applicable,
these drawings
fied using Military Standard nomenclature
where ap- include
re -
plicable.
straint
2.
Antenna
system
drawings,
model
data,
and
takeup
mechanisms/devices;
tracks;
catapults/rockets
operating gear, stabilizing and
3. Radome
of emergency escape oper-
ing
characteristics Contractor
4-7.9.17
Instrumeattatian
in ac-
I. Arrangement
showing (in phantom) any adjacent armor,
miscel-
navigational
These drawings will include all supports, panels,
or oil, or hydraulic
mounts; all electrical connectors; all pitot and static 4. Drawings and data for
carbon monoxide detec-
all tion, in
Control
System
airframe
tion or
meas- dr
2. Thermal
will identify,
data for air-conditioning
system, and will include the functional relationships urization systems which cover the helicopter profile
and purposes of
the components. should include an air supply for cooling and demon-
strate
3. CFE design
for
eliminating entrapped moisture
should be indicated.
or systems, or modification
of GFE, are required. 5. Installation drawings and data of acoustical in-
* 4-10
,A6
velcpe of altitude versus
8806
or receiver
6. Anti-icing
sparencies
requiring
protection
in
accordance
with
4-7.9.19
Armor
systems for protection of periscope
lenses, fuel vents, list which follows:
radomes, antecns, and stores 1. Functional diagrams
showing all items of the
7. A.na ytical report of the anti-icing of engine air entire armament
system. These
with the detail specification.
description of the operation of the inle
anti-icing sys- purposes of the items. -he
nterconnection to systems
installation and arrangement draw-
drawings,
loca-
tion
of each control panel in relation to all other control
4-7.9.18.4 Equipment panels in each compartment.
Drawing and data requiiements
include: 3. Helicopter armament
specification 4. CFE armament design data in accordance with
based on the requirements of MIT.-T-7101, system and MIL-D-18300, when CFE armament equipments or
installation drawings, and substantiating calculations
systems, or modification
to fulfill its operating 5. Installation drawings
showing (in phantom) ex-
detail
Drawings and
1. A list of il car ridge
actuated
tank(s) any system, such as canopy jettisoning, hoist cable guil..
6.
Drawings
report covering air 2. Engineering data for each mechanical, hydrau-
refueling capab'lity data such
part. These parts,
or
as the design
headed material,
specifications
contractor
required fled.
mechanical
prop-
and eiectronic
system used
see par. 4-7.13)
bers
helicopter
and
MIL-F-7179.
This
specification
-Revised
pages
evaluation, consisting
of a summary technical de- An inventory record will be furnished
in accordance
MIL-T-5578 for
mented specifically
virormental
and MII.-T-5422: AV -
cations or specification control drawings. and (2) -clia- 2000, Section 4, for reliability;
AR 70-10 for
bility and maintainability
for radio interfer-
quired in pars. 4-4 (A). 4-4 (5), and 4-7.8. After
ence
approval
consummation of ih' testing, qualification
test reports
verifying compliance
17,
submitted
for
foliows:
priate
subsystems,
when
formal
demonstration
with
with
MIL-F-wihML-547(elgtn)orM
ap- ing on instrument panels, in
accordance
with
and as-
crew furnishings as follows:
a. Fixed seats and manual egress (crash
and
in-
drawings required in par. 4-7.9.8(7), 4-7.9.9, and 4- flight) structural and functional
tests, in ac-
and brake as- Ato
analytical
gov-
erned
6.
6ndeIiacdneih
b.
Fire
detector,
suppression,
and
prevention
unit
revision
8683 or
and equipment
MIL-H-18325
coidance
with
MIL-T-18607
for ad
Minor
not requiring
appr
5440,
f. CI-E external fuel tanks
surveys,
and
h. Armor ballistic
with must be submitted for approval by the procuring ac-
Chapter
i. Cart ridge-actuated devices
to meet the objectives
j. Nonstandard parts
7 and 9, including
a-7 dures, test progress reports and final reports
verifying
6729,
for
measure-
vionics
which 7.
failing
by a 10.
11. External
onding changes may be measured and a
13. Hydraulics
and pneumnatic';
complete list
in report
of design
DRAWING LIST applicable data previously submitted. This list will ref-
erence contractor letters
4-7.15.1
Preparation
cepted, and will show estimated submittal dates
for
b_ pre- data not yet submitted. The summary should list
each
cles
to
be under the contract, excluding the transmittal letters accompanying data submitted
ernment-furnished component.. Thc term "equipment
under
that
paragraph.
neered, material articles; the contract end-itemb, con-
tractor-furnished components, and parts; contractor-
4-8 REPORTS AND DATA
and spares and repair
Darts. Drawings and associated data will be prepared in Reports will be prepared in accordance with MIL-
accordance with MIL-D-l000
S'FD-, I, except as specified herein A Table of Con.
will
contain information sufficient for the intended use tents should be provided when necessary
to
tacili.ate
source of all engineering data used
in the
be
drawn. Drawings
will be prepared and/or revised to ports and data will
be typewritten and in accordance
reflect Class I design changes (as defined in MJL-STD-
with MIL-D-5480; nonreproducible copies
480
and
MIL-STD-481) CSPA-designated Class 11 de- accordance with Type I Class Iand re roducible copies
sign
changes in time to of accordance with Type Class Nonreproducible
microfiln copics at
least 30 days prior
to delivery of the drawings will be in accordance with MIL-D-5480,
first equipment article affected by the change.
They
other Class II changes (I) when Classified
data and drawings
will contain the
is
days
following delivery of the cations, photographs, etc., and on each
drawing
in ac-
last article in the production block to which the draw- cordance with th- existing security regulations.
ings apply, whichever
4-7.15.2
Consolidated
Drawing
List
ACTION
A complete, consolidated list of engineering draw- Quantities, distribution, and submittal dates
of re-
quired data and documentation will be as specified
in
tom as the detail design progresses. This list must be Table 4-1 and in DD Form 1423. Where data and
complete in order to define the current configuration in
documentation are
generated by the contractor as the
depth, and to provide an audit trail of the helicopter result of the suggestions of the Helicopter Engineering
system. Revisions to the list will reflect periodic addi- Handbook Series, and where no specific requirements
tions or revised drawings resulting
from design reviews
activity,
the contractor should retain copies in his files for infor-
steps. The current list,
periodically revised ts agre.-x
activity
during
upon
by
the contractor and tbe CSPA, will
be furnished design reviews or other milestone points which may he
to the CSPA and
final form the desired.
PARAGRAPH
TITLE
OFDATA
E 1ECTIROMAGNET
C CGMP116tIETIT
-.R4 'EMS AND4UASYSTEMSND4OVE[RNMENTTEST
IACTDRSEINGI.IEEIINO PLAN - APPROVAL WNNIPTRODUCIIE. RECURPFINT.
4A- DES'GN R fEWS_ RE IE4 NYL1NRIERODUIEEL NUMREC.UHHITN NYOTAIEP T~tANSCHEILED
DATE OY ThE[
-6
HELICOPTERFWSCII.P
APPROWN
NOT)TEPR)DUT
4-j
47 ENGINEER~ING ATA _____
-44A. PAGPOSTOGRAMSFORNVESTIGATIONS 90 DAYS
AT.GOVLRWMENT FACT)ITIES APPROVAL
PROPOSEDi FORiVEST-GVTTN
AT OTHERRIVATELY
4-T AETRIGYNAMICND I
4
(,AIQRIPGKS - -- . . . - . -DURINU TEST AND'OT LPON COWEkETIONDL A
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wi_.RPFUCtIRlE
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AIRODYNAA4T LST DATA ?fPDRT S _ ST ~ PJPEPRDOCI.BII Rk(IARING --- --- -TRCMPIITO NES;ATOS
4.T.T13, ILWTERMODE)
EST REPORT ~ RE7)15W
NCINREPRODO-i&E N~IONRECUJRRING R D A Y A F E C O L T O N F I V S T G T N .
4-FIR) F R ANALYSREUIS - APP4.JVRt .P0uIL
.TTLIJN
F PRO)GRAM
4-7,2.2 FtEIGFITSIIRAu.ATORROURYJRREPORT .A(CCIPTANCI t*CTRhLPFO1DOCIEIT RECURR~fING EkIDAYS PRIOR TO
INITIATIO 0; fli)GRAM --
42.3 AERODYNAMICSTlABIL'ITYAND CONTITEL INITIAL REPORT 11.3 AYS AE'ILA AWARD OF C.ON.
-4.7.2.3 INITIAL REPORT - 'REIE
4-7.7.3 __ UPDATED REPORT jREVIEW NONTIEPFRODCIRLE RIECUITING CYJARTEFTE
4-7.2.3 T.FPIIVY DATA ACEAFIREDWVITH
4.7.4121 ESTIMATED)
WEIGHTANDP AANCE REPORTH APPROVAE NONAiLPRODOCILE TEON~lRE NG T) DAYS AFTER -CNIC
-4-7.41-) EOI ANDDAIANCE STATUSREYORTS -- AYPPROJAI' -I N I R L R D C F IRECURRINE ATECLASTB1-MONTHER
4.7.414) CALCULATEDWEIGHTREPORT APPROVAL NONREPRODOCIRLE RECIRFINO AS REQUIIREDYCONTRACTDATA EOS LIST
4-7.TISI SAMPLECHARTS A, AND F FOR HANDBOOK
- - AN AT-TB-RI) APPRODVAL.REPPODYTCIE j RECURFARING Y3
DAYS PRIOR To FIRSTFLIGHT
G101 _
'4.7AiRi POST
DESIGNWFillI ANALYSTSREPORT
APPROVAL INCNRD
4-7.112
APPR OVAL
R-.11
ENGINEERI
PRIOR TO CORMLETIONOf CONTRACT
O5REROIICRLE I--ONRECOIFREING
__
~RCT AI AA
-'IEGOGISTIC SuPIOrD~AlLPORTS
RE"'.
4-7. 843 REVIEMDSGTVL AA~EW~ NONREPRRDUC'8. RCURIN 90 n DAYFC GTTAACT~
WARD
IEU
-4.7.9-1 --
OPAW-NOr
4.7.9.5 'WNCOMRIOINDUE7CAT DANN
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47 9In- I EAtEDIEID
49.TI1 LANGI]NE,GEAR
4.'7-9.1 LANDING GEAR
4.7
9.11
1ANDINCG
-47 9.12 .1ENGINE
TI ON. DEEAILED DRAWNG..-
9. 1DESIGN DCA.A.- TNI$ ANDPIPING APROVAl. 'REPROUCILE ' RECURRING AN44.755 AND0 EPORTSIREEWIRED PRIORO
4-7 9, 12(1 PERFGICIVANCL
CON ROl
47.9.13
SYSTEM.
RECUERRING I
14 11 AC. A.D.EETIALLA
RCRING ___ ___
4-7 9.18101 ELECTRICALQUIPMENTNSTALL TIOPI
- . ___ DRAWINGS APPROVAL IREPRODUCIBLE RECURRING _____
4.-79.14 NONSTgAARDOLC6TRCAL EOIPMEN
I ATA APPN7VL
=-
SPECIFICATION
473. 1b4) Cr5 AVIONIC DESIGN LIA AP
ROVAL _ REfRUO5'5tIBCE~ RL___
. . . . . .EL9JIPWIENI
-7917
4.7 919 CREW TATIONS. EURNIS~iNGS.
AND--
4 739.152
PRGAHTTEODAAKIND
OP:
TYPEOPF
SUBMITTAL
4_ 9 a-.1-82 i OXYGENSYSTEMNSTALLATIC
A, INGS0 APPROVAL
REPFXUDLC,&E TiEFCRfN -
i_7 9.18.3,2I
FRPR/UAtV.ATO.DTILDDAIG
A.T
4.9 9.19
AEARI AND
REPECODUOi8LL RECURRING. . _ __
MENT
DRAWINGS
APPROVAL
PEPIFJDUOIW.E
RECURRING-_____
4.9
9,4913)
HELICOPTER
AFIEAMENT
-,ARACSEEIISTIC
rE
41.9311951 AfWJ0 ;NSTALLATIONDRAWINGS APROJVAL EE
T
RGLUDIRLE.TP.CUINTI,
FIRI/
SJRI/IVALTYALSI
EPT
APPROVIAL
NONREFTRODUCIKE
ONETYC-URELING_.-.-
4-I 9.RiIii LISTOF CARTRIDGE ACTUATED1 EVI5CS REVeIW YCNRERoOUGIRE EIr"FCIJr~IiG _____
4.-7 9.F21 EGINEERMA4GATAk r08~NiT ANDA]F6O
PARTS
APPROVAL
fPIJDUCIW.
- AND EVALUATION
0ATS
RIOR
ACCEPTANCE
OP
_4 11
[RISE s
APPIIOVAI ECNPEPR0OIJCIRE
4.7 13141 FIRE
LANS MIST lBESUBAMITTED T
4.7 12TG
HAIINC AND
N R P O C I L REU G
4-7 137151 ANTI-ICING. OEPOGL4ITIE. ND DEERIOSTINEYAPRVL RRNREPR5iL EDoC R - - - - --,
4-7 124151 CAR WAHINGADCHANING AND AAR V L 4 I R N E R D C R E EURN
47 111E
4-7.134161
RECURRING -
CARTRIDGES __ APPROVAL NONTEPRODUCIE RECURRiNG ____ __
ECURRING __ J___
AND1
4-1171 800150 N ICIS I S P O E T O APPROVAL YNONREPRDUCIIE RECURRING
4- 1.IRE7iN GDP LGTNNRETC1O
_
Ai-7147i..I
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4-7 14) ECECTRE)MAONETICOfMPAIIITR APPROVAL JNDNREPIRODUCREE NONRECUARRINGAENTATION
REST RESUBMITTEDAND APPROVED
4.7 I LTII)
j30 DAYSPRIORTO START
4-4 441131 I-UITDSoE
4-714016) GROUNDS)JEPORTEEDUIPELNI
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AND0CON4SOLIDATEDOCRIARING
TEP
AECEPTAN
4
fOP
5
Governmental tests in The
accordance
completion
specifications
requirements will be returned
in DD Form 1423 and
and to proceed with the follow-on development
and prior to
release for manufacture.
All CSPA comments
forwardirg letter.
and approval
ings,
re-
The procedure which follows may be employed to lease, approval, acceptance, or review (information
accomplish expeditious release of
ta-when it is
heli-
te gadothe s bforprvisontiaing ease; piehould m copter. Actions will be designated for A my review and
ted to the CSPA
be sent concurrently to the procuring activity
for re-
furnished with
the for particular
longer interval the
applicable AQF and DD Form 1423.
vised by the reviewing
the Summary
end, be prominently
displayed in the
paragraph. The contractor may issue After the acceptance of approved
drawings, the
limited purchase orders for long lead-time
items as well ture which
do not conflict
with or change
once the basic line
fled in DD Form 1423. All
letters forvarding
approval, or accept-
or acceptance
standards refer-
authorized deviations,
or requests
submitted under
separate forwarding
fi -
Consultation with the
in his
i ouit thi- needs
of
parts,
the CSPA does not assume responsibility for of the particular case. Such action,
or
form, action, normally
fit,
could be initiated by the
assemblies. The responsibility
his sub-
subsystems, and
ance,
and
governing contract documents,
accnm-
DOCUMENTATION
afforded by omission of
Data and documentation requiring
re:vised
may be identi- AQS.
data are acceptable to the Army and
have
without
furnished to all ad- specified in Table
4-I--the contractor will submit
ity, revisions, or
4-9 MODIFICATION
and common sense considerations iidicate the desiia- proposed AQS (par.
4-2).
4-21
4(
4-7.9.1
will
consist
of fully dimensional front elevation, bly tabulated for clarity, where necessnry as follows..
side elevation, and plan views of the iclicopter, aCLU- a. Overall helicopter length, height,
and span
rately portraying
ght,,,
surfijees,
antennas,
arid
other
visible
fea-
()Lvladsai
oiin
o
hes
ks
tures. 'rhe scale of the drawings will ht: 1/20th unless )Lv ladsac sion(owhesi,
otherwise
specified
vertial diStance,.
and overall height
in hoisting attitude
The horizontal reference
skid
geats,
three-point static attitude at
ing gear strut, position of doors and fairings for retract-
able
also
necessary ito establish
the ground lines
(1)
(3) Vertical reference
line level. Ildeuitifv
frorn reference line to
Imnes
propeller or tilted rotor ground clearances oir
i. Angle between :-ei o lift awis of wing and pro-
4.22
line and
75%, a. tinri,ontal and vertical dt,,ances fron refer-
and 90%
CG
the
6. Miseltlaneous surfaces,
ers, flaps, slats, speed brakes, and tabs
ground line
a. Type
of
c. Chord
e. Angular
of
horizontal grounC'
wheels
a.
Tread
a. Gross displacement of hull, each main float.
wheels horizontal reference
line (static posi-
and each auxilia;y
c. Tire
empty, normal gross wtight, and tnaxinium
e. Skid length
overload gross weight
d Ground line with helicopter
on amphiHious
8. Clearances
gear, static
(1)
zero and auxiliary
following: hull or
rotor guards
ward keel
rotor(s)
waterline
at
to each
and
depth
i. Location
propeller helicopter gross weight condition and height from cen-
d. Minimum critical propeller or tilted
rotor tip
clearances attainable
above load water-
shock absorbers and/or tires line and propeller clearance above %aterline
and fully deflected skids, including flat tires or float
on main or auxiliary gear. Ground line to k. Applicable data (Item 7) for wheeled portion
which measured shall be
the physical be of actual size and shap:e
to depict mounting
ing
compatibility
and operating
shall accommodate
ered.
sufficient to enable
the contrac-
shall be
tor to continue with the design of the actual helicopter marked
clearly with the appropriate
with reasonable assurance
that the general arrange- descriptive name. Items subject to relocation such as
ment
removable
demandtiatiwheels,
protectisshcovers,
anddremovable
demo
The-
up. Provisions
for mainte-
The use of 1,xaduction materials in the construction avienic subsystems, gearboxes, and fuel system shall be
of the full-scale
in-)ck-up is not
represent
should be requisi-
they may be on
prior to the
termine routing of items such as cables
and lints. Ac-
and size of the heli- equipment shall be included
in
the
mock-up.
The size and location of e capc hatchcs andi ener
enineering design
of gency provisions for both crew and passengers shall k'-
general oonfiguratioi
unloading
sions
tion, and
and motion films of a simulated eer-
and for post-crash
The maintainability features gercy evacuation should be provided for a
slow-speed
accessibil- evaluation of potential
hazards to the occupants
controls, equipment, or
structure. The mock-up
scheduled maintenance also shall be demonstrated.
simulations of equipment for evaluation in the heli-
Other design features
compartment,
and
doors, windows,
landing Cockpit's) s*all be completely mocked
up and
be demonstrated.
The mock-up shall be configured to allow
the actual trols for retractable
iandimg
terior shape or size. Flexibly
mounted
equipment-
hoists, external auxiliary fuel stores, weapon
racks, oi normal and
equipment,
includi
gmirrors,
micro-
compo- phones, headphones, etc. All furnishings and equip-
nents, the helicopter skins
may be replaced locally with ment shall duplicate the production articles as closely
see-through to facilitate observation and demon- as possible in size, shape,
and
life rafts, seat pads,
handholds, access hatches, and work platforms defined when applicable Seats shall
be of exact size and shape
in the helicopter design. Environmental such
if applicable, crew seats shall be capable of adjust-
as windshield vipers and
crew design
and measurement
controls, and displacertients shall be identified in ac-
The
MIL-STD-1333, and
33515.
special equipment items, and instructions such as their normal envelope, although they need not operate
"BATTERY", "NO STEP", and "NO HAND their respective rotors or surfacs. Control
friction
de-
and
point fueling attachments shall be
shown in relation to to limit all control movements
to those anticipated for
personnel requirements and to permit evaluation of the actual helicopter. The neutral positions of he cyclic
required operations such as removal of filler caps or the control shall be simulated. Control locks, when appli-
insertion of the pressure.fueling probe.
cable,
hatches, win-
dows, etc.,
sta-
the
overa
depicted
and accuratel
if applicablc.
steps,
to stand outside
trip an entrant or
provided
shall
simulate as closely
,:t include intermr
thickness of panels,
those of
individual paper,
gency exits
passenger compartment
quired instruments
tiedown
acco,rino-
dations
to estab-
apart from the lish compatibility with
,tandardiz,:d loading
receive/discharge
shall be demonstrated
to
1. The
mock-up shall
permit evaluation
size
and
bulk
portant
environmental
constraints
in range or force of
constraints of winter clothing and personal field gear
as
effects of
by an
abnormal helicopter
Appendix
viewing,
is the abi;ity
of the typical
in the mock-up ground
crew to effect the
up,
Power
components,
transmissions,
mock-up
subsystems.
sequence
Rearrangement of Appendix
minimum
loading/unloading
times may result, as well fabricated in sLmficient detail to perform all required
as elimnation of
be a prototype
sy,-ie~it.
conmpletcly mocked
up including propellers (if applica- All major items of thehydraulic and pneumatic %ys-
hie), engine
intakes, tens shall be mocked up, including main and emer-
alternate doors,
5-2.1.6 Armament and
configuration or com- The
allow
evaluation
hoisting provisions, as
dummy tanks, filler units, oil coolers, oil reservoirs, applicable, The fixed and movable weapons, turrets,
piping, valves, fittings, drains, and
disconnects. and fire control equipment shall permit the full range
The fuel system shall be mocked up, including
of movement. Particular
dummy tanks (with auxiliary tanks, internal and/or showing all armament installations in such detail that
external), filler units, piping, important valves, fittings, clearances (both ground and structural) and physical
drains, disconnects, dummy aerial refueling probe, and arrangement can be readily
checked.
The arrangemert
fuel dump outlet, as appropriate, shall be such that loading and unloading of gun ammu-
The APU shall be completely mocked
up and
demontiratcd.
5-2.1.4 Electrical/Electronic System
include the armor
Mock-up controls, wiring, and liquid-carrying lines, as well as
flight crew stations.
mocked up, including control panels, generators
and/or alternators, batteries, voltage regulators,
trans-
lubricating sys-
tems
for
completely mocked up, including ducts,
piping,
and valves,
Electrical
sight
be evaluated.
An in-
blade section should be available during
~the mock-up review of the hub
and root blade assem-
techniques
All items of electronic equipment, including com-
of amock-up hub to support the weight f the full-scale
munication
and
use of conventional mock-up
and console structure, antennas, materials and complicate construction. Therefore, a
masts, and lead-ins. Cabling need be simulated only in completely detailed, full-size mock-up of the hub with
the vicinity of the terminating equipment.
representative
5-4
A[
compatibility of
folding. Landing gear mock-ups may not always
be essential.
folding nay
be manual or may be powered by If they are required, they shall conform to the
require-
any
of
land-
ing
"SAFE-UNSAFE"
permit
of accessibility to the helicopter for person-
motions of
gear
Retractable landing gear mock-ups shall demon-
mock-up need not be made
in
retraction mechanism, fair-
provisions. The kine-
provisions shall be
the
for order to
the fail-safe security
of the locks, doors, hatches, or special exterior equipment while in
The mock-up of the hub and rotor blaoec, sall in- any of the intermediate landing
gear positions during
the the retraction or extension cycle. The mock-up shall
swashplate, control rods,
a
the
blades.
The
and
transmit mechanical power
boxes,
along with their associated
couplings and drive tion of transparent panels to the mock-up structure will
shafts, sometimes are
and assist
mock-up. Oil-level sight gages An alternate means
of supporting
gross weight of ground
position should be eri-
ployed for helicopters
incorporating retractable land-
rangement of control bell cranks and tubes may suggest ing gear. The size and
shape
of operation in
of landing gear
the mock-up. The tail rotor shall be mocked up com- clearance and
operation.
pletely, including full-length blades, landing gear spring rate or load
deflectioil characteris-
Helicopters
whici have tail booms and tail rotors tics is not warranted
or desired
at the of loads and weights which would be
imposed
on the
extreme end of the tail group. This may a part the mock-up
structure.
member
and exterior
shall be part of the actual mock-up, in accordance with lighting shall be constructed. The lighting mock-up
the considerations of par. 5-2.3. If it is a simple guard inspection should
be conducted as
soon as possible
be
exhibited
the materi- mock-up s al be employed
for exterior lighting inspec-
employed for crew stations (except for
of the
passenger stations, cargo compartments,
actual
helicopter
be
provided,
when
5i-5
'p: ,.
cockpit or cockpit section cannot
be
employed
cockpit lighting mock-up,
the cockpit
may be simu- ity, light intensity, and flash frequency at the required
lated The framing, windows,
patterns may be determined, and correc-
and/or copilot shall duplicate those of
the
production
on
the
airframe.
5-3 MOCK-UP
shall present
power
availabLie
to
and
clerical
assistance
be
made for viewing the The contractor shall provide a data package to the
mock-up in a completely
ing complete
darkened
ioom
or
red
goggles
shall
be
provided
for
at
from
the
pit lighting mock-up
2. Recommended
checklists prescribed
2.rRecommended chgcklistsmp
rescribed byethespro-
nstalle he
ei pe
tnelicopter.
of instruments
4. Description of features requiring demonstra-
be used. Where controls
with
military
cannot
be
actuated
missions
shall be energized by switches eiternal to the mock-up 5. External visiop
plot, illustrating
or by internal switches not normally employed
for the vision around the helicopter from the crew's normal eye
mock-up inspection. Adjustable
Equal Area projecion
to be plots
and the 6. Photometric data, as appropriate,
prior to
shall be prov-
lighting mock-up inspection.
ided to permit
detail specification, preliminary draw-
5-2.4.2
Exterior
Lighting
Board
members
and
other
evaluators,
The location of exterior
lighting shall be included
by the contractor
Specific evaluation procedures
official mock-up demonstration.
5-6
SEPARATELY (VERSUS INTEGRATED OPERATION)?
EQUIPMENT?
?OINT
6. IF LITTERS ARE PROVIDED,
CHECK
TO
b. HEIGHT OF TOPMOST LITTER ABOVE AN IN-FLIGHT STABLE SURFACE
c. AISLE SPACE BETWEEN LITTERS
motion picture photographs, special lighting, and
crew/passenger compartment to determine
fuselage for various operatioral functions may be
system definition
The rnock-up inspection
in the passen-
contractor's plant for inspection of the mock-up on the ge compartment. The size of the hatches, particularly
date established
by the procuring activity, for the crew, may be influenced strongly by the access
Standardized design
be
used by the Mock-up Review Board to Internal equipment obstruction will be evaluated
augment and/or provide
of using the console, in-
of the mock-up. The inspcction team should have suffi- strument panel,
and seat bottoms or seat backs as steps
cient time to review the mock-up, take
measurements, to facilitate
rapid egress from
are
not compromised by external fuselage
projections such
nel in the 5th to the 95th percentiles who ere wearing as pitot heads or antennas which might
injure the per-
sonnel
provide the mock-up
night lighting
checklists and
tions.
Measurements will be made of seat, panel, con- with appropriate documentation o