Archive / FAA Parachute Rigger Handbook / FAA Parachute Rigger Handbook: Chapter 5

Chapter 5

Chapter 5 — Part 7

FAA-H-8083-17 (2015 Change 1)

PIA-TS-108.1

40 LB PULL TEST: PASSED

DATE: 14 JUN 2009

MASTER RIGGER: JOE RIGGER 1234567

Example of completed test

FIGURE 5

Page 8 of 8

Change 1 (December 2015)

Department of Transportation

Federal Aviation Administration

Aircraft Certification Service

Washington, DC

TSO-C23d

Date: 6/1/94

Technical Standard Order

Subject: TSO-C23d, PERSONNEL PARACHUTE ASSEMBLIES

a. Applicability.

(1) Minimum Performance Standards. This technical standard order (TSO)

prescribes the minimum performance standard that personnel parachute assemblies must meet in

order to be identified with the applicable TSO marking. New models of personnel parachute

assemblies that are to be so identified and that are manufactured on or after the date of this TSO

must meet the standards set forth in Society of Automotive Engineers, Inc. (SAE) Aerospace

Standard (AS) Document No. AS 8015B, “Minimum Performance Standards for Parachute

Assemblies and Components, Personnel,” dated July 7, 1992.

b. Marking. Each personnel parachute assembly or separate sub-assembly must be

marked in accordance with 14 CFR part 21, section 21.607(d) and paragraph 4.2 of SAE AS

8015B. This marking requirement applies to any previously approved major component/sub-

assembly used in this TSO.

c. Data Requirements.

(1) In addition to the requirement in part 21, section 21.605, the manufacturer

shall furnish the manager of the Aircraft Certification Office (ACO), FAA having geographical

purview of the manufacturer’s facilities, one copy each of the following technical data:

(i) A complete description of the personnel parachute assemblies,

including detail drawings, material identification and specifications.

(ii) Operating instructions and limitations, to include donning, retention,

adjustment, and deployment.

(iii) Installation instructions and limitations.

(iv) A report of the tests conducted in accordance with SAE AS 8015B

for qualification and approval of personnel parachute assemblies.

DISTRIBUTION: ZVS-326; A-W(IR)-3; A-X(CD)-4; A-FFS-7, 8(LTD); A-X(FS)-3;

AFS-600 (2 cys); A-FAC-0(MAX)

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(v) Detailed maintenance instructions, including specific guidance on the

limits of wear and damage permissible to webbing material that would warrant replacement.

(vi) The quality control inspection and functional test specification to be

used to ensure each production article complies with this TSO, as required by part 21, section

21.605(a)(3) and part 21, section 21.143(a)(3).

(2) The manufacturer must furnish to the user of the article one copy of the data

and information specified in paragraphs c(l)(ii) and c(l)(v). This data and information is

necessary for proper installation and use and for continued airworthiness of the product or

article.

“The conditions and test required for TSO approval of this article are minimum

performance standards. It is the responsibility of those desiring to install the article

either on or within a specific type or class of aircraft to determine that the aircraft

installation conditions are within the TSO standards. The article may be installed

only if further evaluation by the applicant (user/installer) documents an acceptable

installation and is approved by the Administrator.”

d. Availability of Referenced Documents.

(1) Copies of SAE AS 8015B may be purchased from the Society of Automotive

Engineers, Inc., Department 331, 400 Commonwealth Drive, Warrendale, PA 15096.

(2) Federal Aviation Regulations, part 21, subpart O, may be purchased from the

Superintendent of Documents, U.S. Government Printing Office, Washington, DC 20402-9325.

(3) Advisory Circular 20- 110, “Index of Aviation Technical Standard Orders,”

may be obtained from the U.S. Department of Transportation, General Services Section,

M-443.2, Washington, DC 20590.

/S/ John K. McGrath

Manager, Aircraft Engineering Division

Aircraft Certification Service

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DISTRIBUTION STATEMENT: All Rights Reserved. No Part of this publication may be reproduced without prior written permission from Parachute Industry Association. PIA Headquarters, Parachute Certification Standards Committee, 3833 West Oakton Street, Skokie, IL 60076 Phone: 847-674-9742 Fax: 847-674-9743 or

website www.pia.com for contact details.

Disclaimer: This document is published by the PIA to provide technical and engineering standards that can be used by reference by all those who may benefit from them. The use of this document is entirely voluntary, and its applicability and suitability for any particular use, including any patent or trademark infringement

arising there from, is the sole responsibility of the user. There may be errors, especially in numbers. PIA disclaims any responsibility for accuracy. The PIA reviews each technical publication periodically, at which time it may be reaffirmed, revised, or canceled. The PIA invites your written comments and suggestions.

Parachute Industry Association (PIA)

TECHNICAL STANDARD 135

PERFORMANCE STANDARDS

FOR

PERSONNEL PARACHUTE ASSEMBLIES

AND

COMPONENTS

1. SCOPE:

This document defines the performance standards for personnel parachute assemblies (and

components thereof) to be carried in aircraft for emergency use by aircrew and those reserve

parachutes worn by parachutists for intentional jumping.

This document covers three types of personnel carrying parachute assemblies and the operating

limitations for each:

1.1 PARACHUTE TYPES:

1.1.1 Single harness reserve parachute assembly.

1.1.2 Single harness emergency parachute assembly.

1.1.3 Dual harness reserve parachute assembly.

1.2 MAXIMUM OPERATING LIMITS, GENERAL:

1.2.1 A single harness parachute assembly (or components thereof) may be certified for any maximum

operating weight and for any maximum pack opening speed equal to or greater than 150 KTAS

(277.8 km/h).

1.2.2 A dual harness reserve parachute assembly (or components thereof) may be certified for any

maximum operating weight greater than 500 lb (227.3 kg) (with 250 lb (113.6 kg) in each

harness) and any maximum pack opening speed equal to or greater than 175 KTAS (324.1

km/h). Note that the maximum operating weight need not be the same for each harness.

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1.3 LIST OF TECHNICAL STANDARDS, TABLES AND FIGURES:

Figure 1 Multiplier Factors for Structural Overload Testing

Figure 2 Functional Direct Drop Tests Required per 4.3.8.1

Table 1 Data Marking Requirements

Table 2 Human Factors and Actuation Force Tests – Primary Actuation

Device/Ripcord

Table 3 Performance Test Requirements

Table 4 Performance Test Requirements for Component Qualification

2. DEFINITIONS AND GENERAL REQUIREMENTS

2.1 GENERAL DEFINITIONS:

For the purposes of this document, the following definitions are used:

a. “Administrator” – The FAA Administrator or equivalent chief executive of the cognizant

agency and/or his designated subordinate personnel and/or designated subordinate

organization acting on his behalf and with his authority in the matter concerned.

b. "Airspeed, Calibrated" (KCAS) means the indicated airspeed of an aircraft, corrected for

position and instrument error. Calibrated airspeed is equal to true airspeed in standard

atmosphere at sea level.

c. "Airspeed, Equivalent" (KEAS) means the calibrated airspeed of an aircraft corrected for

adiabatic compressible flow for the particular altitude. Equivalent airspeed is equal to

calibrated airspeed in standard atmosphere at sea level.

d. "Airspeed, Indicated" (KIAS) means the speed of an aircraft as shown on its pitot static

airspeed indicator calibrated to reflect standard atmosphere adiabatic compressible flow at

sea level uncorrected for airspeed system errors.

e. “Airspeed, True” (KTAS) – means the airspeed relative to undisturbed air. True airspeed is

equal to equivalent airspeed multiplied by (0/) ½. where 0 is the air density at standard day

conditions and  is the air density at the local altitude.

f. "Approved", unless used with reference to another person, means approved by the

Administrator for use within the limits specified by the manufacturer and verified by

compliance with the requirements of this standard.

g. “Canopy”- The part of the parachute that opens up and fills with air and provides the lift

and/or drag required to decelerate the payload to the desired value.

h. “Certified”, unless used with reference to another agency, means certified by the cognizant

agency as having met the requirements of this standard.

i. “Cognizant Agency” – The governmental agency or other organization tasked with oversight

or regulation of aviation activities within a given geographical area or country. e.g. the

Federal Aviation Administration (FAA) within the United States, the Joint Airworthiness

Authorities (JAA) within the European Union and similar agencies worldwide. In some cases,

the cognizant agency may delegate part or all of its authority to a subordinate agency such

as a national aero club.

j. “Drogue” – A small aerodynamic decelerator towed behind a falling body to slow its velocity.

k. “Manufacturer” – The person (or business/corporate entity) who controls the design and

quality of the article produced including the parts of them, and any processes or services

related to them that are procured from an outside source.

l. “Main Assisted Reserve Deployment (MARD) device” – An automatically releasable

connection between the main parachute and the reserve deployment system which uses a

malfunctioned main canopy to speed reserve deployment upon breakaway.

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m. "Parachute" means a device used or intended to be used to retard the fall of a body or object

through the air.

n. “Parachutist in Command” – means the person making a tandem jump who:

(1) Has final authority and responsibility for the operation and safety of the jump;

(2) Has been designated as parachutist in command before the jump; and

(3) Holds the appropriate rating for the conduct of the jump.

o. “Passenger parachutist” means a person who boards an aircraft, acting as other than the

parachutist in command of a tandem parachute operation, with the intent of exiting the

aircraft while in-flight using the forward harness of a dual harness tandem parachute system

to descend to the surface.

2.1.1 MAJOR COMPONENTS:

For purposes of this document a parachute assembly normally, but not exclusively, consists of

the following major components:

a. Deployment control device such as a sleeve, bag, diaper, or functional equivalent.

b. Deployment initiation device (pilot chute, drogue, or functional equivalent) and bridle.

c. Canopy(s) including suspension lines, reefing device, and connector links (if used).

d. Riser(s), when not integral with harness and/or canopy.

e. Stowage container(s) or stowage pack(s).

f. Harness (es).

g. Primary actuation device (ripcord or functional equivalent).

h. Reserve static line.

i. Drogue canopy and bridle (if used with reserve and/or emergency parachutes).

j. Drogue release device (if used with reserve and/or emergency parachutes).

2.1.2 SINGLE HARNESS RESERVE PARACHUTE ASSEMBLY:

A certified parachute assembly that is worn in conjunction with a main parachute assembly and

used by one person for premeditated jumps. This includes, as applicable, the reserve

deployment initiation device, deployment control device, canopy, risers, stowage container,

harness, primary actuation device, and reserve static line.

2.1.3 DUAL HARNESS RESERVE PARACHUTE ASSEMBLY:

A certified parachute assembly used for premeditated jumps by two people: a parachutist in

command and a second parachutist (each in his/her own harness), utilizing one main parachute

assembly and one reserve parachute assembly. This assembly includes, as applicable, the

reserve deployment initiation device, deployment control device, canopy, risers, stowage

container, harness, primary actuation device, and reserve static line.

2.1.4 MAIN PARACHUTE ASSEMBLY:

A non-certified parachute assembly that is worn in conjunction with a certified reserve parachute

assembly as the primary parachute (the one intended for use) for premeditated jumps. The main

parachute assembly shall consist of the main container and all associated parts of the main

parachute that are not permanently attached to the certificated harness assembly.

2.1.5 SINGLE HARNESS EMERGENCY PARACHUTE ASSEMBLY:

A certified parachute assembly that is worn by one person for emergency, (unpremeditated) use

only. This assembly includes, as applicable, the deployment initiation device, deployment

control device, canopy, risers, stowage container, harness, and primary actuation device.

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2.1.6 FAILURE OF A PARACHUTE ASSEMBLY OR COMPONENT:

The term “failure” in this document shall mean any change in a component or assembly that

adversely affects its airworthiness. However, the use of consumable, frangible or single use

parts shall be permitted in all assemblies and shall not be considered a failure if they function as

designed.

2.1.7 FUNCTIONALLY OPEN:

Functionally open shall mean a parachute sufficiently deployed and inflated to provide a rate of

descent of not more than 24 ft/s (7.3m/s). This condition may be demonstrated by video, film or

electronic data of the test in a manner determined by the manufacturer.

2.1.8 RESERVE STATIC LINE (RSL):

A device connected to the main parachute assembly that is capable of actuating the reserve

parachute assembly following a breakaway from the main canopy.

2.1.9 MAIN PARACHUTE BREAKAWAY DEVICE:

A device used by the parachutist in command to separate the main parachute from the harness

of a single or dual-harness reserve parachute assembly. The parachutist in command shall be

able to operate the main parachute breakaway device for dual harness reserve parachute

assemblies.

2.1.10 MAXIMUM OPERATING WEIGHT (MOW):

The maximum operating weight is the total (gross) weight of all individuals or dummies and their

equipment including the parachute assembly itself. MOW is also known as the “placard weight”.

2.1.11 MAXIMUM PACK OPENING SPEED (MPOS):

The maximum pack open speed in KTAS (knots true airspeed) is the maximum speed at which

the (reserve/emergency) parachute pack (container) is designed to be opened. This definition

specifically allows for the wearing of parachutes in freefall and/or in aircraft at speeds higher than

the maximum pack opening speed. MPOS is also known as the “placard speed”.

NOTE: In order to provide an inherently greater margin of safety without requiring that tests be

conducted at all possible altitudes, all test conditions in this document are stated in KEAS and

that all maximum pack opening speeds are stated in KTAS. In the event that a manufacturer

elects to conduct further testing at higher altitudes, the placard limits may be changed to reflect

any test conditions successfully conducted.

2.1.12 MINIMUM OPERATING WEIGHT (MinOW)

The minimum operating weight is the lowest allowed total (gross) weight of an individual or

dummy (or all individuals or dummies in the case of a tandem) and their equipment including the

parachute assembly itself. The MinOW shall be specified by the manufacturer and may be any

weight demonstrated to be appropriate by the manufacturer for the system.

2.1.13 SERVICE LIFE RESTRICTED ITEMS:

Materials or products that, by design, are service life restricted for any reason (environmental,

structural, chemical, etc.) may be used in any manner chosen by the manufacturer. Each such

item must be marked in a manner that will allow maintenance personnel to determine the

serviceable status of the part.

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3. MATERIALS AND WORKMANSHIP:

Materials and workmanship shall be of a quality that documented experience and/or tests have

conclusively demonstrated to be suitable for the manufacture of, and appropriate for the intended

use in, personnel parachute assemblies. All materials shall remain functional for storage from

-40 to +200F (-40 to +93.3 C), and from 0 to 100% relative humidity. All plated ferrous parts

shall be treated to minimize hydrogen embrittlement.

4. DETAIL REQUIREMENTS

4.1 DESIGN AND CONSTRUCTION:

4.1.1 MATERIALS:

All materials shall be designed to support the proof loads specified in the applicable

specification, drawing, or standard, without failure. In the absence of an applicable specification,

drawing, or standard for a particular material, successful completion of the qualification tests

listed under section 4.3 shall be considered adequate evidence of suitability.

4.1.2 STITCHING:

Stitching shall generally be of a type that will not ravel when broken. Note that this is not

required for consumable or frangible parts.

4.1.3 MAIN PARACHUTE ASSEMBLY:

When installed but not deployed, the main parachute assembly shall not interfere with the proper

function of the reserve parachute assembly. Ref: Table 2

4.1.4 PRIMARY ACTUATION DEVICE/RIPCORD:

The primary actuation device/ripcord, including all joints, shall withstand the test loads of 4.3.2

without failure. The primary actuation device/ripcord shall meet the human-factors requirements

of 4.3.3., if applicable.

4.1.5 RESERVE STATIC LINE (RSL):

The reserve static line, if used, including all joints shall withstand the test loads of 4.3.2 without

failure and shall meet the functional requirements of 4.3.8.2.

4.1.6 HARNESS RELEASE:

The harness shall be so constructed that, after landing, the parachutist can separate himself

from the main and reserve canopies and/or harness assembly unaided. On a dual harness,

reserve parachute assembly, the parachutist in command must be able to separate himself and

the second parachutist from the reserve canopy and/or harness assemblies unaided.

4.1.7 DROGUE PARACHUTE ASSEMBLY & RELEASE:

For reserve or emergency parachute assemblies, incorporating a drogue, the drogue release

shall be tested at an equivalent force to the drag force generated at the MOW and MPOS.

The human release force shall not be less than 5 lbf (22.2N) and must not exceed 22 lbf (97.9N).

The release shall meet the human-factors requirements of 4.3.3.

4.1.8 DATA CARD POCKET; STOWAGE CONTAINER:

The stowage container shall be provided with a parachute data card pocket constructed such

that the card will not be easily lost and will be readily accessible, when the parachute is packed

in the container.

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4.2 MARKING REQUIREMENTS:

Marking requirements are listed in Table 1.

NOTE: The data items listed in Table 1 need not be marked at the same location on the

component as long as all of the pertinent information is permanently marked.

4.2.1 MARKING, STOWAGE CONTAINER - OPERATING LIMITS:

The minimum and maximum operating limits in Table 1 shall be marked/placarded on or

attached to the outside of the parachute stowage container (pack). The marking/placard may

refer to the owner‟s manual for the minimum operating weight. The lowest maximum operating

weight of any component in the assembly (canopy, harness, etc.) and the lowest maximum pack

opening speed of any component (canopy, harness, etc.) shall be marked on the outside of the

stowage container (pack) in such a location as to be readily available to the user during donning

of the parachute assembly and subject to a minimum of obliteration during use.

This information may alternately be placed in a pocket marked with the legend „Operating

Limitations Inside‟; the pocket must be readily available to the user during donning of the

parachute assembly and subject to a minimum of obliteration during use.

NOTE: The maximum pack opening speed and minimum and maximum weight markings shall

be in a block typeface, in a minimum size of 0.375 inch (9.5 mm) tall (27 point type). The other

information required by Table 1 may be marked in another location, if desired.

4.2.2 MARKING, CANOPY - STATEMENT OF USE:

Each certified canopy shall be marked to show its approved use as follows:

4.2.2.1 “Single Harness Emergency Parachute Canopy”

“Single Harness Reserve Parachute Canopy”

“Single Harness Emergency/Reserve Parachute Canopy”

“Dual Harness Reserve Parachute Canopy”

4.2.2.2 Each canopy (single harness types only) that has not been tested in accordance with the

breakaway tests of Section 4.3.8.2 shall be marked as follows:

“LIMITATION: May not be used with main parachute breakaway device”.

4.3 QUALIFICATION TESTS:

The minimum performance standards listed in Tables 2, 3 and 4 shall be met. There shall be no

failure to meet any of the requirements during the qualification tests of this section. In case of a

failure, the cause must be found, corrected, and all affected tests repeated.

4.3.1 PACKING METHOD:

The packing method must be specified and the identical packing method must be used for all of

the functional and structural tests.

4.3.2 PRIMARY ACTUATION DEVICE/RIPCORD TEST:

(a) The ripcord, including all joints, shall not fail under a straight tension test load of 300-lbf

(1337.7 N) applied for not less than 3 seconds.

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(b) If the reserve is to be static line actuated by releasing the main canopy, the reserve static

line, if used, must not fail under a straight tension test load of 300-lbf (1334.5 N) applied for

not less than 3 seconds.

not fail under a straight tension test load of 600-lbf (2668.9 N) applied for not less than 3

seconds.

(d) Rigid pins, if used, shall not yield under a load of 8-lbf (35.6 N) applied to the cable (or

equivalent) perpendicular to the axis of the pin, for not less than 3 seconds. The pin shall be

supported for 0.5 in (12.7-mm) maximum at the end farthest from the cable attachment. All

4.3.3 human factors tests shall be performed using a primary actuation device/ripcord that

has passed this test.

4.3.3 HUMAN FACTORS AND ACTUATION FORCE TESTS:

An anthropometrically diverse group of individuals (consisting of a representative group of no

less than 3 males and 3 females) from the intended user group shall be employed for all human

factors tests in 4.3.3. All individuals shall be able to operate the subject device without any

undue difficulty. Table 2 lists the required test conditions and number of tests for each particular

component. Additional information for the component tests is listed below.

TESTS: Under normal design operating conditions, all devices tested under this paragraph shall

result in a positive and quick operation of the device within the following load range applied to

the handle:

(a) a load applied at the handle of not less than 5 lbf (22.2 N), applied in the direction giving

the lowest pull force,

(b) a load applied at the handle of not more than 22 lbf (97.9 N), applied in the direction of

normal design operation,

(d) the primary actuation device shall be tested in accordance with Table 2,

(e) the emergency/reserve drogue release (if used) shall be tested in accordance with Table 2.

NOTE: For these tests, the primary actuation device (ripcord or equivalent) shall be equipped

with a tamper-indicating device (i.e. seal thread or equivalent) of the same type that will be

required for production articles in service.

4.3.4 HUMAN FACTORS TESTS, HARNESS:

Harnesses shall demonstrate that they will perform the basic function of retaining the body at the

end of the parachute suspension system in an inherently secure manner.

This requirement shall be demonstrated by passing all live drop tests in Table 3.

4.3.5 ENVIRONMENTAL TESTS:

Three drops shall be made at 60 KEAS except that prior to the test the parachute assembly shall

be subjected to the following preconditioning: (These tests may be combined with other tests.)

4.3.5.1 Precondition for 16 hours at not less than +200 F (93.3 C), stabilize to ambient and test drop.

4.3.5.2 Precondition for 16 h at not greater than -40 F (-40 C), stabilize to ambient and test drop.

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4.3.5.3 Precondition for not less than 400 continuous hours with a 200 lbf (889.6 N) or greater load

applied to compress the pack in a manner similar to that most likely to be encountered in actual

use. Test drop within 1 hour after removing the load.

4.3.5.4 Alternate preconditioning. The preconditioning requirements for 4.3.5.1 and 4.3.5.3 may be

combined as follows: The complete test parachute assembly may be placed in a vacuum bag

and preconditioned at +180 F (82.2 C) for 18 hours at a constant vacuum of not less than 25”

Hg (0.846 bar). Stabilize to ambient and drop.

4.3.6 STRUCTURAL OVERLOAD TESTS:

No material(s) or device(s) that attenuates shock loads and is not an integral part of the

parachute assembly or component being certified may be used. Tests may be conducted for

either a complete parachute assembly or separate components. There shall be no evidence of

material, stitch, or functional failure that will affect airworthiness. For reusable items the same

items shall be used for all 4.3.6 tests. Peak opening force shall be measured on all 4.3.6 tests.

The parachute must be functionally open within the number of seconds calculated for 4.3.8 tests.

Parachute assemblies shall be tested in accordance with the following schedule:

(a) Test weight = Maximum operating weight x 1.2

Test speed = Maximum pack opening speed x 1.2

-OR-

(b) Test weight = Maximum operating weight multiplied by the factor from Figure 1

Test speed = Maximum pack opening speed multiplied by the factor from Figure 1

However, the test speed must not be less than 180 KEAS (333.4 km/h) for reserve and

emergency parachute assemblies and the test weight must not be less than 264 lb. (120 kg).

For dual harness parachute assemblies the test weight must not be less than 600 lb. (272.7 kg)

and the test speed must not be less than 200 KEAS (370.4 km/h).

4.3.6.1 STRENGTH TEST, COMPLETE PARACHUTE ASSEMBLY:

Three drops shall be made with weight and speed in accordance with 4.3.6. When using test

method (b), in 4.3.6 a 4th drop must be added using the same parachute under the same

conditions in the first three drops. Where non-positive locking hardware is used to attach the

canopy or riser(s) to the harness, a cross connector must be used and one of the above drops

shall be with only one attachment engaged to test the cross connector and hardware.

4.3.6.2 STRENGTH TEST, ALTERNATE MEANS OF COMPLIANCE CANOPY (ONLY):

Three drops shall be made with a gross weight and speed in accordance with 4.3.6. When using

test method (b), in 4.3.6 a 4th drop must be added using the same canopy under the same

conditions in the first three drops. A test vehicle (e.g., a bomb) may be used. The canopy and

any required additional components (i.e., deployment device, pilot chute, and risers) shall be

tested as a unit. The connector links (if used) shall be attached to the risers in the same manner

as the intended use and the riser(s) should be secured to the test vehicle in a manner

appropriate to the test objective. For example, if the parachute risers are to be tested on the

bomb drop, it should be arranged in a manner as to duplicate the loading found on the personnel

parachute harness. Where non-positive locking hardware is used to attach the canopy or

riser(s) to the harness, a cross connector must be used and one of the above drops shall be with

only one attachment engaged to test the cross connector and hardware.

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4.3.6.3 STRENGTH TEST, ADDITIONAL MEANS OF COMPLIANCE HARNESS (ONLY):

A harness may, at the manufacturer‟s option, be placarded with a higher average peak opening

force than what was measured in 4.3.6 tests by performing additional tower drop tests as

outlined below:

The harness shall be drop tested using a torso shaped dummy, three (3) times for each of four

(4) different loading conditions.

The dummy weight shall be not less than 75% of harness maximum operating weight and the

drop distance shall be as necessary to generate the required forces.

Up to three (3) separate harnesses may be used; however each harness shall be subjected to a

minimum of one test at each of the following four test conditions.

(a) Test condition one – All risers loaded to a combined load of at least 100% of placard

maximum load.

(b) Test condition two – Only left side harness/canopy attachment point(s) loaded to a

combined load of at least 66% of placard load.

(d) Test condition four – Each unique brake setting shall be tested to a minimum of 16.7% of

placard load if applicable.

4.3.6.4 STRENGTH TESTS, ALTERNATE MEANS OF COMPLIANCE, DROGUE CANOPY (ONLY)

For parachute assemblies in which a drogue parachute canopy is an integral part of the reserve

or emergency parachute assembly, the drogue may be separately tested at the conditions

determined in 4.3.6. The drogue canopy itself and all related components of the drogue

assembly must be tested as a functional subsystem of the parachute assembly.

4.3.7 FUNCTIONAL TESTS (Twisted Lines):

A minimum of 5 drops shall be made with a weight not more than the maximum operating weight

dummy or person1 in each harness. The airspeed at the time of pack opening shall be 60 KEAS

(111.1 km/h)

Procedural Note: The suspension lines shall be twisted together (360 degrees) three times in

the same direction within the upper one third of the suspension line length beginning immediately

below the attachment point to the canopy. The twists shall be placed in the lines before the

suspension lines are stowed.

Performance Requirement: The parachute must be functionally open within 133% of the time

calculated in 4.3.8 from the time of pack opening.

4.3.8 FUNCTIONAL TESTS (Normal Pack - All Types):

Opening Time or Altitude Loss: Using the MOW in pounds and the MPOS in KTAS for all 4.3.8

tests the maximum allowable opening time and the maximum allowable altitude loss on any drop

shall be determined from the following formulas..

(a) The greater of 3.00 seconds or the value determined as follows:

A person‟s or individual‟s body weight may be increased to equal the maximum operating weight by using a weight belt or simil ar device.

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Opening Time Allowed (sec.) = (MOW – 250) * 0.01 + (MPOS/150 * 3.0)

-OR-

(b) The greater of 300 feet or the value determined as follows:

Altitude Loss Allowed (ft) = (MOW-250) + (MPOS/150 * 300)

4.3.8.1 DIRECT DROP TESTS:

There shall be a minimum of 48 tests at weights and airspeeds (at the time of pack opening) as

outlined in Table 3. The test condition airspeeds are in KEAS. From the time of pack opening,

the parachute canopy must be functionally open within the allowed time or altitude as calculated

in 4.3.8.

(a) The manufacturer shall specify the Maximum Operating Weight and the Minimum

Operating Weight.

(b) The Maximum Pack Opening Speed (MPOS) shall not be less than 150 knots.

overload testing in Paragraph 4.3.6

(d) The manufacturer will be allowed to select whether to measure altitude loss or opening

time, but within each block on the test grid the same method must be used.

(e) The maximum allowable opening time shall be calculated using the formula in 4.3.8(a):

there shall be a minimum of 4 successful tests for each block; the opening times will be

averaged and presented to the Administrator in the format shown in Figure 2.

(f) The maximum allowable altitude loss shall be calculated using the formula in 4.3.8(b):

there shall be a minimum of 4 successful tests for each block; the altitude loss must be

averaged and presented to the Administrator in the format shown in Figure 2.

(g) The opening times and/or altitude loss for each test block will be averaged and published

in the format shown in Figure 2 in the owner‟s manual or in some other readily available

location.

NOTE:

If a “MARD device” option is offered, an additional 8 drops at weights and airspeeds (at the

time of pack opening) must be performed as outlined in the Table 3 with the MARD attached.

4.3.8.2 BREAKAWAY DROP TESTS (systems with main canopy release):

Eight drop tests shall be made by breaking away from an open and normally functioning main

parachute canopy and actuating the reserve parachute within 2 seconds of the breakaway.

These tests shall be conducted by a person (or suitable other devices) weighing not more than

the maximum operating weight. The initial vertical velocity shall be less than 20 ft/s (6.1 m/s) and

the total velocity less than 36 ft/s at the time of breakaway. From the time of pack opening, the

parachute canopy must be functionally open within the altitude or within the allowed time as

calculated in 4.3.8.

NOTE:

(a) If a reserve static line is part of the assembly, then 4 of the breakaway drops shall be

made with the reserve static line actuating the reserve pack.

(b) If a “MARD device” option is offered, an additional 16 drops at weights and airspeeds (at

the time of pack opening) must be performed as outlined in the Table 3 with the MARD

attached.

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4.3.9 RATE OF DESCENT TESTS (METHOD 1):

Per Table 3, there shall be not less than 6 drops, with an individual and/or dummy in each

harness weighing not less than the maximum operating weight2. The average rate of descent

shall not exceed 24 ft/s (7.3 m/s) and the total velocity shall not exceed 36 ft/s (11.0 m/s) in an

unaltered post deployment configuration, corrected to standard day sea level altitude conditions.

The rate of descent measurement shall be taken over a minimum interval of 100 ft (30.5 m).

These tests may be combined with other tests in this section.

4.3.9.1 RATE OF DESCENT TESTS (METHOD 2):

The rate of descent corrected to standard day sea level altitude conditions shall not exceed 5

ft/sec (1.5m/sec) at touchdown with appropriate control manipulations and the average rate of

descent shall not exceed 24 ft/sec (7.3 m/s) in the unaltered post deployment configuration over

a minimum interval of 100 ft (30.5m). These tests may be combined with other tests in this

section.

NOTE: If the total velocity exceeds 36 ft/sec at maximum certified weight, the container or

harness (if integral to the container) must be marked in an area readily visible to the user: “For

experienced parachutists only. The owner‟s manual contains experience requirements.”

4.3.10 STABILITY TESTS:

Per Table 3, there shall be not less than 6 drops, at the minimum operating weight. The

oscillations shall not exceed 15 from the vertical, in an unaltered post-deployment configuration.

These tests may be combined with other tests in this section.

4.3.11 LIVE TESTS:

Per Table 3, there shall be a minimum of 4 live tests with an individual weighing not more than the

maximum operating weight in each harness. Two drops shall include a freefall of not more than 3

seconds and 2 drops shall include a freefall of at least 20 seconds. These tests may be

conducted in conjunction with functional and/or rate of descent tests when practical. The user(s)

must suffer no significant discomfort from the opening shock and must be able to disengage

himself (themselves) unaided from the harness after landing. For this test the standard harness

may be altered to permit attachment of a certified reserve parachute assembly (less harness)

provided that such alteration does not interfere with the normal operation of the parachute

assembly being tested. Reserve parachute assemblies shall be tested with the main

compartment(s) full and empty, with a minimum of two tests each.

NOTE: Live tests for Dual Harness Reserve Parachute Assemblies may be tested with the

parachutist in command and a dummy payload in the passenger harness.

5. COMPONENT QUALIFICATIONS:

Any single component, assembly of components, group of components or group of assemblies

may be certified. Table 4 lists the appropriate test paragraphs for each of the major components.

Any components not listed in Table 4 shall be tested according to all applicable sections of this

document based on the components function.

A person‟s or individual‟s body weight may be increased to equal the maximum operating weight by using a weight be lt or similar device.

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5.1 COMPONENT COMPATIBILITY:

The component manufacturer shall provide a means of determining compatibility and shall

provide specific guidance to ensure that form, fit and function of all components, as assembled,

are within acceptable limits for each individual component and the assembly as a whole.

5.2 COMPONENT QUALIFICATION BY GROUP:

Components may be qualified as a group consisting of a range of scaled sizes. Separate

elements of the component design may be linearly scaled at different rates as specified in the

component drawings provided that fit, form, and function are not adversely affected. For

canopies, the range may consist of scaled sizes to a maximum area of three times the smallest

size.

When certifying components as a group, only the largest and the smallest members of the group

must be tested in accordance with the appropriate sections of this document.

5.3 MAINTENANCE REQUIREMENTS:

The manufacturer of each component is responsible for developing and disseminating the

maintenance requirements for each component, specifically including the inspection interval,

repack cycle, service life, criteria for continued airworthiness and the qualifications required of

maintenance personnel.

5.4 FITTING REQUIREMENTS:

The manufacturer is responsible for developing and disseminating instructions identifying the

correct method of fitting the equipment to the user.

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1.00

1.50

2.00

100 150 200 250 300

Multiplier

Maximum Pack Opening Speed for Placard (KTAS)

PIA TS-135 - Figure 1

Multiplier Factors for Structural Overload Testing

Per Paragraph 4.3.6

Airspeed Multiplier Weight Multiplier Resultant Kinetic Energy Factor

PIA TS-135 Figure 2

Direct Drop Tests

Per Paragraph 4.3.8.1

Test Speed

Test Weight 60 KEAS 85 KEAS MPOS x 80% MPOS x 100%

Minimum Operating

Weight

4 4 4 4

Averaged Operating

Weight*

4 4 4 4

Maximum Operating

Weight

4 4 4 4

Minimum Total (direct drop) Functional Tests Required 48

*Averaged Operating Weight is defined as (Maximum Operating Weight + Minimum Operating

Weight)/2

Average test weights shall be +/- 5%

Minimum test weights shall be +1%/-10%.

Maximum test weights shall be +10%/-1%

1.43

1.1

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Marking Data Requirements

Reference Paragraph

Deployment Initiation Device (Pilot Chute,

etc.)

Deployment Control Device (d-bag, etc.)

Reserve Emergency Canopy

Stowage Container

Primary Actuation Device (Ripcord or

Equivalent)

Reserve Static Line (if used)

Harness (if not integral with container)

Risers (if not integral with harness)

Reserve/Emergency Drogue Canopy & Riser

(if used)

Reserve/Emergency Drogue Release Device

(if used)

Manufacturers Name, Code or Symbol X X X X X X X X X X

Part Number (w/dash numbers) X X X X X X X X X X

Serial or Lot Control Number X X X X X X X X X

Date of Manufacture (month and year minimum) X X X X X X X X X

Date to Be Removed from Service (if applicable) X X X X X X X X X

Maximum Pack Opening Speed (KEAS) 4.3.6 X X X X X

Maximum Gross Weight (lb) if applicable 4.3.6 X X X

Minimum Gross Weight (lb) 4.2 X

Average Peak Force Measured during 4.3.6 tests 4.3.6 X X

Appoved for Use Statement 4.2.2 X

Statement of Authorization Under TS0-C-23e

and/or (J) TSO-C-23e if applicable X X X X X X X

Operators Warning Label with Maximum

Operating Limits 4.3.6 X X

Operators Warning Label and location for

component operating limitations 4.2.1 X

Operators Warning Label with Maximum Total

Velocity for intended use (Student, Tandem,

Emergency Air Crew or Other). 4.3.9 X

Maximum Drogue deployment speed 4.3.6 X

For ripcords, either lot control number or date of manufacture may be marked provided that tracabillity is maintained

At a minimum, Maximum Operating Limitations must include maximum pack opening speed and maximum gross w eight. Manufacturer may

voluntarily derate operating limitations.

Redundant marking may be eliminated for components w hich are permanently joined at the time of manufacture. If this is the case, the marking

w ill be located on the most visible component, normally the container.

PIA-TS-135 - Table 1.

Data Marking Requirements

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Male Female Male Female Male Female

P/F Force Standing

Upright N/A N/A N/A N/A 6 6

P/F Force Standing

Upright N/A none/with N/A Full 3 3 3/3 3/3

P/F Force Standing

Upright N/A none/with N/A Empty 3 3 3/3 3/3

P/F Force Suspended

Harness 1g none Main Risers Empty 3 3 3 3

P/F Force Suspended

Harness 1 g with Main Risers Empty 3 3

P/F Force Suspended

Harness 4.1.7 N/A Drogue N/A 6 6

P/F Force Suspended

Harness 4.1.7 none Drogue Full 3 3 3 3

P/F Force Suspended

Harness 4.1.7 none Drogue Empty 3 3 3 3

P/F Force Suspended

Harness 4.1.7 with Drogue Full 3 3

P/F Force Suspended

Harness 4.1.7 with Drogue Empty 3 3

Notes:

2. N/A = Not Applicable

3. P/F = Pass/Fail

4.1.7 - The drogue release shall be tested at an equivalent (or greater) force to the drag force generated at the MOW and MPOS.

PIA-TS-135 - Table 2

Human Factors and Actuation Force Tests

Primary Actuation Device / Ripcord

Dual Harnes s Res erve

Parachute As s emblyData

Required

Suspended

Single Harnes s Res erve

Parachute As s embly

Main

Pack

Conditio

Te st

Condition

Load

Factor

1. All tests must be conducted with a reserve/emergency canopy assembly packed for intended use.

24/12Total Tests Required in This Section (drogue / no drogue) 60/36

Emergency Parachute

Asse mbly

30/18

Additional tests if emergency/reserve drogue is used:

Primary Actuation Device / Ripcord

Second

Parachutis t

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Dummy Live Dummy Live

1, 8, 5 Primary Actuation Device/Ripcord Test 4.3.2

1,2,5 Human Factors and Actuation Force Tests 4.3.3

Human Factors Tests, Harness 4.3.4

Environmental Tests 4.3.5

1, 3, 5 Precondition to +200 F 4.3.5.1 60 KEAS <= MaxOW

1, 3, 5 Precondition to -40 F 4.3.5.2 60 KEAS <= MaxOW

1, 3, 5 Precondition - compressed pack 4.3.5.3 60 KEAS <= MaxOW

1, 3, 5 Precondition - alternate to 4.3.5.1 & 4.3.5.3 4.3.5.4 60 KEAS <= MaxOW

Structural Overload Tests 4.3.6

1,2,3,5 Complete Assemblies 4.3.6.1 Fig. 1 Fig. 1 N/S 3 3

1,2,3,5 Alternate Means of Compliance, Canopy Only 4.3.6.2 Fig. 1 Fig. 1 N/S 3 3

1,2,3,5 Alternate Means of Compliance, Harness Only 4.3.6.3 Fig. 1 Fig. 1 N/S 3 3

1,2,3,5 Drogue (if applicable) 4.3.6.4 Fig. 1 Fig. 1 N/S 3 3

1, 3 (or 4), 5, Functional Tests, Twisted Lines 4.3.7 60 KEAS <= MOW N/S

1, 3 (or 4), 5, Functional Tests, (Normal Pack all types) 4.3.8

1, 3 (or 4), 5, Direct Drop 4.3.8.1 60 KEAS MinOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 60 KEAS A vOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 60 KEAS MaxOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 60 KEAS MinOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 60 KEAS A vOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 60 KEAS MaxOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 85 KEAS MinOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 85 KEAS A vOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 85 KEAS MaxOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 85 KEAS MinOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 85 KEAS A vOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 85 KEAS MaxOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 80% MPOS MinOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 80% MPOS A vOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 80% MPOS MaxOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 80% MPOS MinOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 80% MPOS A vOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 80% MPOS MaxOW Full

N/A

Total Drops at 85 KEAS

Total Drops at 80% MPOS

IAW Table 2 and as described in paragraphs 4.3.3(a) through (e)

Demonstrated by successful completion of live jumps per paragraph 4.3 .11

Total Drops at 60 KEAS

Emergency

Parachute

Assemblies

Single or Dual

Harness Reserve

Parachute Assembly

Notes on Data

Required Test Description Reference

Paragraph

Speed at Pack

Opening

(KEAS)

Test Weight Main Pack

Condition

IAW 4.3.2 (a) through (d)

N/A

Opening Time allowed shall be calculated IAW paragraph 4.3.8 (a).

Opening Altitude allowed shall be calculated IAW paragraph 4.3.8 (b)

N/A

PIA TS-135 Table 3

Required Qualification Tests

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1, 3 (or 4), 5, Direct Drop 4.3.8.1 100% MPOS MinOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 100% MPOS A vOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 100% MPOS MaxOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 100% MPOS MinOW Full

1, 3 (or 4), 5, Direct Drop 4.3.8.1 100% MPOS A vOW Empty

1, 3 (or 4), 5, Direct Drop 4.3.8.1 100% MPOS MaxOW Full

1, 3 (or 4), 5, 10, 11 Direct Drop “MARD device” 4.3.8.1 60 KEAS <= MaxOW Full

1, 3 (or 4), 5, 12 Direct Drop “MARD device” 4.3.8.1 <= MaxOW Full

1, 3, 5, 9 Functional Tests, Breakaway 4.3.8.2 < 20 fps Vv <= MaxOW Empty

1, 3, 5, 9, 13 Functional Tests, Breakaway “MARD device” 4.3.8.2 <= MaxOW Empty

1, 3, 5, 9, 14 Functional Tests, Breakaway “MARD device” 4.3.8.2 <= MaxOW Empty

1, 3, 5, 9, 15 Functional Tests, Breakaway “MARD device” 4.3.8.2 <= MaxOW Empty

1, 3, 5, 9, 12, 16 Functional Tests, Breakaway “MARD device” 4.3.8.2 <= MaxOW Empty

1, 5, 7 Rate of Descent Tests 4.3.9 N/A MaxOW N/S

1, 5, 6 Stability Test 4.3.10 N/A MinOW N/S

1, 3, 5, 11 Live Jumps 4.3.11 < 60 knots <= MaxOW N/S 2 2

1, 3, 5, 12 Live Jumps 4.3.11 > 120 knots <= MaxOW N/S 2 2

Abbreviations used above:

IAW In accordance with

MPOS Maximum pack opening speed

MaxOW Maximum operating weight

AvOW Average operating weight

MinOW Minimum operating weight

N/A Not Applicable

N/S Not Specified

Notes on Test Critera

1 Record Pass/Fail

2 Record Riser Force

3 Record Opening Time

4 Record Altitude Loss

5 Video Record

6 Record Oscillation Angle

7 Record Rate-of-Descent

8 Record Ripcord Pull Force

9 If an RSL used, then half of the cutaway test shall be connducted with the RSL - a total of 8 tests is required

10 Jumps may be performed concurrently with similar direct drops outlined in table 3

11 Shall include a freefall of not more than 3 seconds

12 Shall include a freefall of at least 20 seconds

13 Breakaways from stable main

14 Breakaways from forward spinning main. Half left spin, half right spin

15 Breakaways from BACKWARDS spinning main. Half left spin, half right spin

16 Breakaways from bag lock malfunction

N/A

Total Direct Drop Tests

Total Drops at 100% MPOS

N/A

PIA TS-135 Table 3 continued

Required Qualification Tests

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PIA TS-135, Revision 1.4, Issued April 22, 2010, Page 18 of 18

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Description of Test

Reference Paragraph for PIA-TS-135

Complete Parachute Assembly

Deployment Initiation Device (Pilot Chute,

etc.)

Deployment Control Device, (dbag, etc.)

Canopy, lines, links, and reefing device (if

used)

Stowage Container

Primary Actuation Device (Ripcord or

Equivalent, Except Static Line)

Primary Actuation Device (Static Line)

Reserve Static Line (if used)

Harness

Risers (if not integral with harness)

Drogue, Canopy & Riser (if used)

Drogue Release Device (if used)

MARD (if used)

Ripcord Strength Tests 4.3.2 X X X X X

Human Factors 4.3.3 X X X X X X

Environmental 4.3.5 X X X X X X X X X X

Structural Overload Test 4.3.6 X X X X X X X X X *1

Functional Tests - Twisted

Line 4.3.7 X X X

Functional Tests - Normal

Pack, Direct Drop 4.3.8.1 X X X X X X X

Functional Tests - Normal

Pack, Breakaway 4.3.8.2 X X X X X X X X

Rate of Descent 4.3.9 X X

Stability 4.3.10 X X

Live Drops 4.3.11 X X X X X X X X X X X X X

*1 MARD installation shall not degrade strength or tensile loads on any reserve deployment devices or subassemblies on which

it is installed. The manufacturer shall prove equivalent strength between similar devices or subassemblies with and without the

MARD installed. This can be done with a bench/pull test or tensile test. For example, the strength of a free bag bridle with MARD

parts installed but not hooked up should not be less than a bridle without a MARD installation.

PIA-TS-135 - Table 4.

Performance Test Requirements for Component Qualification

Change 1 (December 2015)

Department of Transportation

Federal Aviation Administration

Aircraft Certification Service

Washington, D.C.

TSO-C23f

Effective

Date: 09/21/2012

Technical Standard Order

Subject: Personnel Parachute Assemblies and Components

1. PURPOSE. This technical standard order (TSO) is for manufacturers applying for a TSO

authorization (TSOA) or letter of design approval (LODA). In it, we the Federal Aviation

Administration (FAA), tell you what minimum performance standards (MPS) your personnel

parachute assembly and components must first meet for approval and identification with the

applicable TSO marking.

2. APPLICABILITY. This TSO affects new applications submitted after its effective date.

a. All prior revisions to this TSO are no longer effective. Generally, we will not accept

applications for the previous revision after the effective date of this TSO. We may do so,

however, up to six months after it, if we know that you were working against the prior MPS

before the new change became effective.

b. Personnel parachute assemblies and components approved under a previous TSOA may

still be manufactured under the provisions of its original approval.

3. REQUIREMENTS. New models of personnel parachute assemblies and components

identified and manufactured on or after the effective date of this TSO must meet the MPS

qualification and documentation requirements in Parachute Industry Association (PIA)

Technical Standard 135 TS-135 Revision 1.4 issued April 22, 2010 “Performance Standards for

Personnel Parachute Assemblies and Components” as modified by appendix 1 of this TSO.

a. Functionality. This TSO’s standards apply to equipment intended to be used as a

reserve or emergency parachute.

b. Failure Condition Classifications.

( 1) Lose of the function defined in paragraph 3.a is a catastrophic failure condition.

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c. Functional Qualification . Demonstrate the required performance under the test

conditions in Appendix 1 of this TSO.

d. Deviations. We have provisions for using alternate or equivalent means of compliance

to the criteria in the MPS of this TSO. If you invoke these provisions, you must show that your

equipment maintains an equivalent level of safety. Apply for a deviation under the provision of

14 CFR § 21.618.

4. MARKING.

a. Mark at least one major component permanently and legibly with all the information

in CFR § 45.15(b). The marking must include the serial number.

b. Also, mark the following permanently and legibly, with at least the manufacturer’s

name, subassembly part number, and the TSO number:

(1) Each component that is easily removable (without hand tools), and

(2) Each subassembly of the article that you determined may be interchangeable.

5. APPLICATION DATA REQUIREMENTS. You must give the FAA aircraft

certification office (ACO) manager responsible for your facility a statement of conformance, as

specified in 14 CFR § 21.603(a)(1), and one copy each of the following technical data to support

your design and production approval. LODA applicants must submit the same data (excluding

paragraph 5.f) through their civil aviation authority.

a. A manual(s) containing the following:

(1) Operating instructions and equipment limitations sufficient to describe the

equipment’s operational capability.

(2) Describe in detail any deviations.

(3) Installation procedures and limitations sufficient to ensure that the personnel

parachute assembly and component, when installed according to the installation procedures, still

meets this TSO’s requirements. Limitations must identify any unique aspects of the installation.

The limitations must include a note with the following statement:

“This article meets the minimum performance and quality system standards required by a

technical standard order (TSO). Installation of this article requires separate approval.”

b. Schematic drawings, wiring diagrams, and any other documentation necessary for

assembly, installation, donning, and operation of the personnel parachute assembly and

component

Change 1 (December 2015)

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c. Instructions covering periodic maintenance, calibration, and repair, for the continued

airworthiness of personnel parachute assemblies and components. Include recommended

inspection intervals and service life, as appropriate.

d. A drawing depicting how the article will be marked with the information required by

paragraph 4 of this TSO.

e. Identify functionality or performance contained in the article not evaluated under

paragraph 3 of this TSO (that is, non-TSO functions). Non-TSO functions are accepted in

parallel with the TSO authorization. For those non-TSO functions to be accepted, you must

declare these functions and include the following information with your TSO application:

(1) Description of the non-TSO function(s), such as performance specifications,

failure condition classifications, software, hardware, and environmental qualification levels.

Include a statement confirming that the non-TSO function(s) do not interfere with the article’s

compliance with the requirements of paragraph 3.

(2) Installation procedures and limitations sufficient to ensure that the non-TSO

function(s), meets the declared functions and performance specification(s) described in

paragraph 5,e.(1).

(3) Instructions for continued performance applicable to the non-TSO function(s)

described in paragraph 5.e.(1).

(4) Interface requirements and applicable installation test procedures to ensure

compliance with the performance data defined in paragraph 5.e.(1).

(5) Test plans, analysis and results, as appropriate, to verify the function and

performance of the hosting TSO article is not affected by the non-TSO function(s).

(6) Test plants, analysis and results, as appropriate, to verify the function and

performance of the non-TSO functions(s) as described in paragraph 5.e.(1).

f. The quality system description required by 14 CFR § 21.608, including functional test

specifications. The quality system should ensure that you will detect any change to the approved

design that could adversely affect compliance with the TSO MPS, and reject the article

accordingly. (Not required for LODA applicants.)

g. Material and process specifications list.

h. List of all drawings and processes (including revision level) that define the article’s

design.

i. Manufacturer’s TSO qualification report showing results of testing accomplished

according to paragraph 3.c of this TSO.

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6. MANUFACTURER DATA REQUIREMENTS. Besides the data given directly to the

responsible ACO, have the following technical data available for review by the responsible

ACO:

a. Functional qualification specifications for qualifying each production article to ensure

compliance with this TSO.

b. Equipment calibration procedures.

c. Schematic drawings.

d. Wiring diagrams.

e. Material and process specifications.

f. If the article contains non-TSO function(s), you must also make available items 6.a

through 6.e as they pertain to the non-TSO function(s).

7. FURNISHED DATA REQUIREMENTS.

a. If furnishing one or more articles manufactured under this TSO to one entity (such as an

individual jumper or a drop zone operator), provide one copy or on-line access to the data in

paragraphs 5.a through 5.c of this TSO. Add any other data needed for the proper installation,

certification, use, or for continued compliance with the TSO, of the personnel parachute

assembly and components.

b. If the article contains declared non-TSO function(s), include one copy of the data in

paragraphs 5.e.(1) through 5.e.(6).

8. HOW TO GET REFERENCED DOCUMENTS.

a. You can download a free copy of PIA TS-135 Revision 1.4 issued April 22, 2010

Performance Standards for Personnel Parachute Assemblies and Components at:

http://www.pia.com/piapubs/TSDocuments/TS-135v1.4.pdf

b. You can find a current list of technical standard orders and advisory circulars on the

FAA Internet website Regulatory and Guidance Library at http://rgl.faa.gov/. You will also find

the TSO Index of Articles at the same site.

/S/

Susan J. M. Cabler

Assistant Manager, Aircraft Engineering Division

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APPENDIX 1. MINIMUM PERFORMANCE STANDARD FOR PERSONNEL

PARACHUTE ASSEMBLIES AND COMPONENTS

This appendix prescribes the MPS for a personnel parachute assembly and component. The

applicable standard is PIA TS-135 Revision 1.4 issued April 22, 2010 Performance Standards for

Personnel Parachute Assemblies and Components, as modified for this TSO:

1. Page 2, replace Para, 2.1.i. to read as follows:

“Cognizant Agency” - The Federal Aviation Administration (FAA) or civil aviation

authorities recognized in bilateral agreements by the FAA,

2. Page 5, Para. 4.1.2. delete: “generally”.

Stitching should not ravel when broken. “Generally” reduces the requirement for stitch

choice, and adversely impacts the current standard.

3. Page 5, Para. 4.1.3.delete: “Ref: Table 2”.

Table 2 is not relevant to this requirement. Testing of a packed assy will show if the main

parachute will interfere with the proper function of the reserve parachute.

4. Page 9, Para. 4.3.7. in first sentence delete: “a weight not more than”.

The worst case is the maximum operating weight.

5. Page 11, disregard paragraph 4.3.9.1., Rate of Descent Tests (Method 2).

We omitted the Method (2) testing, for not providing an equivalent level of safety to

current standard. This method is directed at high performance and experience parachutists in

sport and skydiving activities. Novice or less experienced parachutists in emergency conditions

due to incapacitation, panic, etc., may not be able to safely deploy and land.

We have to consider the safety of all jumpers, not just the highly skilled, highly experienced.

It is argued that the risks the experienced jumpers are exposing themselves to, are mitigated by

their skill and experience.

To allow the increased velocity may improve the safety of highly skilled, highly experienced

jumpers, but it erodes the safety for the beginner, incapacitated, panicked, or a jumper who has

gotten himself into a treacherous landing area.

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We do not agree that a canopy manufacturer can demonstrate that a jumper can safely land with

an appropriate control manipulation while performing a flare before touchdown. This approach

relies on jumper’s experience to meet the MOPS that parachutes have been certified to. This

approach does not provide an equivalent level of safety.

6. Page 14, Table 1, under Marking Data Requirements, replace:

Statement of Authorization under TS0-C-23e and/or (J) TS O-C-23e if applicable.

With

Statement of Authorization. Unde r TSO-C23f and/or ETSO-C23f if applicable.

TSO-C23e has been cancelled

Change 1 (December 2015)

Original source PDFPublished from pages 289–319 of the recorded source chapter.

Open source PDF ↗