SPECIFICATION FOR PILOT'S 

OPE OK 

GAMA SPECIFICATION NO. I 

Issued: February 15,1975 

Revised: October 18, 1996; Revision No. 2 

prepared by 

General Aviation 

Manufaeurers Association 

Copyng ht Q 1 996 by 

General Aviation Manufacturers Association 

Washington, D.C. 

All rights reserved. No part of this book may be reproduced in any 

form without permission in writing from the publisher. 

SPECIFICATION FOR PILOT'S OPERATING HANDBOOK 

Rev. Date 

Rev. 1 

(Og/O 1 /84) 

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LOG OF REVISIONS 

Description 

Revised preface page. 

Revised preface page con?. 

Revised title. Rev. para. 3A, 6, 7 & 10. 

Revised para. 0.1 ,O.3, 0.5, 0.7. 

Revised para. 0.9, 0.11, 0.13, 0.15, 0.17. 

Revised para. 0.19, 0.21, 0.23, 0.25, 0.31. 

Revised para. 0.33, 0.35, 0.41, 0.43, 0.45, 0.51. 

Revised Figure 0-1. 

Revised Figure 0-2. 

Revised Figure 0-3. 

Revised Figure OA. 

Revised Figure 0-5. 

Revised Figure 0-6. 

Revised para. 1.1, 1.3, 1.11, 1.13. 

Revised para. 1.21, 1.23, 1.25, 1.27, 1.29, 1.31. 

Revised para. 1.31 con't. 

Revised para. 1.31 con't. 

Revised para. 1.31 con't. 

Revised para. 2.1, 2.3. 

Revised Figure 2-1. 

Revised para. 2.5. 

Revised para. 2.7, 2.9. 

Revised para. 2.1 1,2.12 and Figure 2-3. 

Revised para. 2.21. 2.23, 2.37, 2.39. 

Revised para. 3.1, 3.3, 3.5, 3.7. 

Revised para. 3.9, 3.9(a), 3.9(b), 3.9(cj, 3.9(dj, 3.9(e), 3.9(fl, 3.9(9), 3.9(h). 

Revised para. 3.9(i). 

Revised para. 3A. 1, 3A.3, 3A.5. 

Revised para. 3A.7, 3A.9. 

Revised para. 4.1 ,4.3, 4.5, 4.7. 

Revised para. 4.9, 4.13, 4.15, 4.17, 4.19. 

Revised para. 4.1 9 con't. 

Revised para. 5.1, 5.3, 5.7, 5.9, 5.11, 5.13, 5.15. 

Revised para. 5.35. 

Revised para. 5.37(e), 5.37(i). 

Revised para. 5.41 (9. 

Revised para. 5.41 (1) 5. 

Revised List of Figures. 

Revised page. 

Revised page. 

Revised tile. Revised para. 6.1, 6.3, 6.5, 6.7, 6.9. 

Revised para 6.9 con?. 
Rev. 1 

(cont) 

8-2 

9-1 

LOG OF REVISIONS 

Description I 

Revised title. Revised para. 7.1. 

Revised para. 7.33. 

Revised para. 7.51. 

Revised para. 8.1, 8.3, 8.9. 

Revised para. 8.15. 

Revised para. 9.1. 9.7, 9.9. 

Revised title. 

I 

Division, ACE-100 

Revised: September 1, 1984 

Description I 

Revised log page 

Revised preface page 

Revised para. 3.9(a), 3.9(9) 

Revised para. 4.9, 4.15 

Added para 5.42 Performance Presentattons in lcrng Conditions 

Revised para. 7.25(a), 7.25(g) 

Added safety tips (5) 

' ~ichael Galtagher, ~anagr 

Aircraft Certification Division 

Small Airplane Directorate, ACE-100 

Revised: October 18, I996 

Rev. Date 

Rev 2 

(1 Of 1 8/96) 

Page 

No. 

... 

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10-1 
PREFACE FOR REVISION 2 

This revision of GAMA Specification No. 1 incolgorates NTSB suggestions for inclusion of emergency procedures for 

supercharger/turbocharger failure, safety tips for operating in icing conditions and use of child restraint seats and normal 

operating procedures for short field and soft field landings. It also establishes, per FAA, the limitations of use of $he 

specification for showing compliance with FAR 23.1581. The limitation applies to all editions of the specification and is 

as follows: 

GAMA SPECIFICATION NO. 1 LlNlITATlO 

Pilots Operating Handbooks prepared in accordance with "GAMA Specification No. I", as revised through Revision No. 2, 

dated October 18, 1996, are appropriate for showing compliance with CAR 3, Paragraph 3.777, and FAR 23, Paragr'aph 

23.1581 on airplanes having a certification basis including FAR 23 through Amendment 23-44 except Commuter Category 

(Ref. FAR 23 Amendment 23-34, Amendment 23-39 or both). 

PREFACE 

This Spe%ication was developed by representatives of member companies of the General Aviation Manufacturers 

Association for use in preparing Pilot's Operating Handbooks thata. Are of maximum usefulness as an operating reference book for pilots; 

b. Meet government regulatory requirements* where applicable; and 

c. Meet industry standards for scope of material, arrangement, nomenclature and definitions. 

This Specification is designed to provide guidance for the preparation of Handbooks for all types of general aviation 

airplanes originally certificated at maximum takeoff weights of 12,500 pounds or less (or 5,700 kg). Consequently, not all 

of the material in the Specification is applicable to any one model and provision is made for manufacturers to omit 

material inappropriate to specific aircraft types or models. Thus, the Specification provides flexibility in Handbook 

preparation based on the complexity of the airplane while maintaining a high degree of standardization of arrangement, 

definitions, and performance information. 

The rules of construction followed in the preparation of this Specification are the same as generally used by the FAA in the 

preparation of its rules (See Federal Aviation Regulation 1.3). "Shall" is used in the imperative sense (that is, when there is 

an obligation to act in the manner specified). The word "shall" is also used in the imperative sense when there is a choice 

of more than one manner of fulfilling the obligation to act. In such cases, the right to choose between alternatives belongs 

to the Handbook (airplane) producer. For example, see Section 5, Performance, Paragraph 5.9 Format Options. This 

paragraph requires a presentation of data in one of only two formats - graphical or tabular. No other format is permissible. 

Which to use, graphical or tabular, is a choice completely up to the Handbook (airplane) producer. 

When a right or privilege is conferred upon the producer of a Handbook, the word "may" is used. When a right or privilege 

is abridged, the words "may not" are used. Except when a specific layout, style, format, standard, etc., is required (or when 

a choice must be made from a specified list) the producer of the Handbook (airplane) may use whatever layout, style, 

format, standard, etc., he chooses. Except when the Handbook producer is restricted in choice or otherwise limited, the 

choice is his. 

The sequence of topics in the Handbook is intended to increase in-flight usefulness. For example, the Sections on 

"Limitations" and "Emergency Procedures" are placed ahead of "No& Procedures," "Performance," "Weight and 

Balance" and other Sections to provide easier access to information that may be required in flight. 
The units used are those which will be of most value to pilots. Calibrated Airspeed (GAS) is to be used only as necessary to 

comply with any applicable requirements of the certificating authority as the pilot works exclusively with Indicated 

Airspeed (IAS). Also KNOTS are used throughout to avoid the co&ion between knots STS) and miles per hour (MPH' 

in performance charts and tables. 

Derived terms, such as "Density Altitude," are not used. Charts and tables are constructed so that they may be used with 

data directly available, such as pressure altitude and temperature. 

The Specification contains little, if any, new material or novel approaches. Basically, it is a guide to industry 

standardization of proven concepts to be presented in a form most useful to pilots. 

The Federal Aviation Administration has reviewed this Specification and has ". . . determined that a handbook that would 

meet the specification would also meet the intent of the requirements in FAR 23, which is to provide the pilot with all of 

the information needed to operate his aircraft in a safe manner." The Federal Aviation Administration recognized that 

compliance with this Specification will result in a high degree of standardization of content and format for all aircraft types 

and this will lead to a level of safety equal to or higher than is required under FAR 23. 

* Note: This Specification refers to various FAA regulations. If the Specification is being used to prepare a Handbook for 

acceptance by an airworthiness authority other than FAA, the appropriate regulations of that airworthiness authority may 

be substituted. 
CONTENTS 

Section 

0 

I 

2 

3 

3A 

4 

5 

6 

7 

8 

9 

10 

Technical Publication Guidance 

General 

Limitations 

Emergency Procedures 

Abnormal Procedures (Optional) 

Normal Procedures 

Performance 

Weight and Balance and Equipment List (if applicable) 

Description of the Airplane and its Systems 

Handling, Servicing and Maintenance 

Supplements 

Safety and Operational Tips (Optional) 

Alphabetical Index (Optional) 

SECTION 0 

TECHNICAL PUBLICATION GUIDANCE 

TABLE OF CONTENTS 

Paragraph Page 

General ............................................................................ 0-1 

Cover Title ........................................................................ 0-1 

Binder Type and Page Sue ............................................... 0-1 

Title Page ................................................................... 0-1 

Table of Contents .............................................................. 0-2 

Page Identification ............................................................ 0-2 

Copy Standards ................................................................. 0-2 

Illustrations, Figures and Tables ........................................ 0-2 

Schematic Diagrams. General ........................................... 0-2 

Schematic Diagrams. Details ............................................. 0-3 

Schematic Diagrams, Legends .......................................... 0-3 

Schematic Diagram Symbols, Devices or Codes ............... 0-3 

Tab Dividers ..................................................................... 0-3 

Contents ............................................................................ 0-3 

Order and Numbering ..................................................... 0-4 

Subject Headings .............................................................. 0-4 

Identifying Revised Material ............................................. 0-4 

Log of Revisions ............................................................... 0-4 

Obtaining Revisions .......................................................... 0-4 

Supplements ...................................................................... 0-4 
INTENTIONALLY LEFT BLANK 
SECTION 0 

TECHNICAL PUBLICATION GUIDANCE 

General 

In order to achieve the objective of providing the 

pilot with required, useful or desirable information 

concerning the operation of the particular airplane, 

in a form reasonably uniform throughout the 

industry, drafters of Handbooks shall follow the 

Specification to the extent practical. Questions of 

compliance with the Specification shall be referred 

to the General Aviation Manufacturers Association 

(GAMA) and the Federal Aviation Administration 

(FAA) for resolution. Significant opinions 

concerning compliance with the Specification shall 

be published. 

Cover Title 

The cover title shall be "Pilot's Operating 

Handbook" or "Pilot's Operating Handbook and 

FAA Approved Airplane Flight Manualn. 

The cover title and applicable airplane designation 

shall be prominently displayed on the cover or spine 

(or both) of the Handbook. Other information may 

be displayed on the cover. 

Binder Type and Page Size 

Handbooks shall be readily revisable. They may be 

in loose-leaf form, with durable, multi-ring cover, 

or permanently bound. If in loose-leaf form 

"standard", or commonly used page sizes shall be 

used. 

Title Page 

The title page (See Figure 0-1) shall contain the 

following information: 

1. The title, "Pilot's Operating Handbook and FAA 

Approved Airplane Flight Manual" for all 

airplanes except those for which the airplane 

manufacturer elected to provide a separate FAA 

Approved Airplane Flight Manual. In the latter 

case, the title shall be "Pilot's Operating 

Handbook. 

Note: After the effective date of this revision, Pilot's 

Operating Handbooks for newly manufactured 

airplanes must be FAA Approved Airplane Flight 

Manuals. 

3. The Handbook producer's (airplane 

manufacturer's) publication identification, if 

applicable. 

4. The airplane serial number and registration 

number if appropriate (leave space for insertion 

of these numbers). 

Note: The backside of the title page should be left 

blank to avoid the need for revision and potential 

loss of the inserted airplane serial and registration 

numbers. 

5. The airplane model number, as shown in the 

FAA Type Certificate Data Sheet or Aircraft 

Specification and, at the Handbook producer's 

option, the type certification number or 

common airplane name, or both. 

6. An applicability statement, prominently 

displayed, and similar to the following example 

(as appropriate). 

"FAA approved in the normal category based on 

FAR 23. This document must be carried in the 

airplane at all times." 

7. In Handbooks for airplanes required to have (or 

for which the airplane manufacturer has elected 

to Provide) FAA Approved Airplane Flight 

Manuals, the statement: 

"THIS HANDBOOK INCLUDES THE MATERIAL 

REQUIRED TO BE FURNISHED TO THE PILOT 

BY THE FEDERAL AVIATION REGULATIONS 

AND ADDITIONAL INFORMATION PROVIDED 

BY THE MANUFACTURER AND 

CONSTITUTES THE FAA APPROVED 

AIRPLANE FLIGHT MANUAL." 

8. For Handbooks that are not FAA Approved 

Airplane Flight Manuals, the statement: 

"THIS HANDBOOK INCLUDES THE MATERIAL 

REQUIRED TO BE FURNISHED TO THE PILOT 

BY THE FEDERAL AUTION REGULATIONS 

AND ADDITIONAL INFORMATION PROVIDED 

BY THE MANUFACTURER." 

2. The manufacturer's name. 

Issued: February 15, 1975 

Revised: October 18, 1996 

0-1 

Q 1996 General Aviation Manufacturers Association 
9. A statement that the Handbook meets GAMA 

Specification No. 1, SPECIFICATION FOR 

mors OPERATING HANDBOOK, dated 

(date of the Specification to which the particular 

Handbook conforms). 

10. The date of FAA approval and signature and 

title of the certificating authority. 

0.9 Table of Contents 

The main text of each section shall be preceded by a 

Table of Contents, listing the paragraph heads in 

numerical page order. Subparagraphs and other 

pertinent information, such as a list of figures, may 

be shown in the Table of Contents of the Section. 

0.11 Page Identification 

The page numbers in each section will include the 

section number and a dash (i.e. "3-" for all pages in 

the "Emergency Procedures" section) followed by 

the serial number of the page beginning with "1" for 

each section, such as 3-1, 3-2, etc. 

Each page shall bear a page number and date of 

issue or revision at the bottom. The page number 

shall be in the lower right corner and the date of 

issue in the lower left corner, for right-hand pages. 

(Figure 0-2) The page number shall be in the lower 

left comer and the date of issue in the lower right 

comer, for left-hand pages. (Figure 0-3) Pages of 

permanently bound Handbooks need not be dated. 

Table of Contents pages shall be dated but need not 

be numbered. 

Each page shall bear the date of the original issue 

until revised and, when revised, that of the latest 

revision. Instead of using the actual date of issue on 

each page of an original issue of a Handbook, the 

words "original issue" may be used. In such a case, 

the Title Page and the Table of Contents pages 

preceding each section of the Handbook shall bear 

the actual date of issue following the words 

"original issue". 

On pages requiring folding, the fold shall be made in 

a manner that permits the page number to be visible. 

Except as provided below, a normal blank page 

within a page block. other than the back of a foldout 

page, shall be identified, with a phrase such as "This 

page left blank intentionally" or "Intentionally left 

blank". 

Instead of printing either "This page left blank 

. intentionally" or "Intentionally left blank" on blank 

pages, the Handbook producer may use dual page 

numbering on pages preceding or following a blank 

page. For example: 3-9 (3-10 blank) or (3-9 blank.3- 

10). 

In the event a page must be added subsequent to the 

initial printing, the page shall carry the number of 

the preceding page with a letter suffix added. The 

added page(s) shall show the following page number 

(e.g. Page 1-6Al1-6B). 

0.13 Copy Standards 

Text my be prepared in one or two columns with or 

without justification. Warnings, cautions and notes 

may be used to highlight or emphasize important 

points. All pages (except wiring diagrams and 

foldouts) shall be printed on both sides. Each section 

shall be started on a right-hand page. The 

manufacturefs masthead, publication title, airplane 

model, and issue or revision date shall appear on all 

pages (that have text, illustrations, figures or tables) 

of loose-leaf Handbooks. 

0.15 Illustrations, Figures, and Tables 

Illustrations, figures and tables may be used. They 

should be located as close as practical to the related 

portions of the text. A list of figures may precede a 

substantial grouping of illustrations, figures and 

tables in a section of the Handbook. 

For ease of reading and cross reference, illustrations, 

figures and tables should be presented in a vertical 

layout, if practical. When an illustration, figure or 

table is reproduced horizontally on a page, the top 

shall be placed toward the left edge of the sheet. 

(See Figure 0-3) 

All illustrations, figures and tables shall be 

referenced in the text as figures or by title (or both). 

Each figure shall iden=ed by a title or a figure 

number. Numbering shall be in numerical 

progression, prefued by the Section Number (e.g., 

Figure 1-1, Figure 1-2; Figure 2-1, Figure 2-2). 

Though techniques such as shading, crosshatching, 

screening or similar means are recommended, the 

use of color is permissible. 

0-2 

@ 1 996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
0.1 7 Schematic Diagrams, General 

Schematic diagrams may be used to indicate "flow" 

and to illustrate the operation of systems such as air 

control, electrical, fluid power, fuel and 

hubosystems. (See Figures 0-5 and 0-6) 

The user of the schematic diagram is the pilot. The 

schematic diagram shall not be created for primary 

use by a mechanic or technician. The schematic 

diagram should tend to deal with an overall system 

rather than with subsystems, e.g., the air 

conditioning system rather than a compressor or 

blower within the air conditioning system. 

The schematic diagram must be of size 

that legends. symbols. devices, codes, etc., are 

readable by persons with normal vision. Turn-page 

schematic diagrams shall be avoided to the extent 

practical. 

In designing schematic diagrams, it may be 

necessary to compromise between detail necessary 

to make the diagram self-explanatory and the 

simplicity essential for ease of reading and 

understanding. Where schematic diagrams are 

complex by virtue of automatic features or 

interrelated controls in the subject system, these 

characteristics should be pointed out by means of 

explanatory text in the diagram, or in the 

accompanying text, or both. 

On schematic diagrams with a large number of listed 

items, (e.g., an electrical schematic) the items shall 

be presented in a logical order, such as the sequence 

of the arrangement of the items in the airplane. 

0.19 Schematic Diagrams, Details 

The flow of the system shall receive prim 

attention. It shall be presented in patterned shading 

with a minimum of turns in the.1ines. Arrows shall 

be used to indicate flow direction when needed to 

understand the schematic diagram. The flow shall 

include the generator, tank, reservoir, or other 

appropriate starting point. The diagram shall be 

arranged so that the flow of the system can be traced 

with a minimum of effort. Crossovers should be 

avoided if practical. Return lines need not be shown 

in entirety unless needed to understand the system. 

A separate shading pattern shall be used for each 

individual system on any one illustration, to 

distinguish between supply, pressure, return, etc. 

Flow control devices within the system, such as 

check valves, fuel pumps, accumulators, and relays, 

should be included. Solenoid valves shall be shown 

with a notation indicating whether the valve is 

spring-loaded to the open or closed position. 

0.21 Schematic Diagram, Legends 

Space permitting, legends shall be spelled out within 

the diagram rather than abbreviated or keyed by 

numerals to a list of legends at the bottom or on an 

adjacent page. No abbreviations may be used unless 

they are universally meaningful. If an obscure 

abbreviation must be used because of space 

limitations, it shall be asterisked and spelled out in 

an unused portion of the image area. When text 

supports the illustration, the text shall employ the 

exact terms used in the illustration. 

0.23 Schematic Diagram Symbols, Devices or Codes 

The same symbol, device, or code shall be used 

throughout the Handbook to depict the same system, 

valve or control. 

Whenever practical, each symbol should physically 

resemble the actual system component depicted in 

the schematic diagram. Abstractions should be 

avoided. If an abstraction must be used, it shall be 

selected from a recognized national standard or shall 

be a box with a title inside. 

0.25 Tab Dividers 

If the Handbook is prepared in looseleaf form, each 

section shall be marked with a plasticized tab 

divider. For ease of reference, the dividers shall be 

staggered. Tab dividers shall indicate section 

numbers or titles, or both. The section containing 

"Emergency Procedures" shall have a red plasticized 

tab divider. Separation of sections in permanently 

bound Handbooks is not required. 

0.31 Contents 

The Handbook shall contain the following sections 

in the order shown 

Section 1 - General 

Section 2 - Limitations 

Section 3 - Emergency Procedures 

Section 3A - Abnormal Procedures 

(Optional) 

Issued: February 15, 1975 

Revised: October 18, 1996 

0-3 

O 1996 General Aviation Manufacturers Association 
Section 4 - 

Section5 - 

Section 6 - 

Section 7 - 

Section 8 - 

Section 9 - 

Section 10 - 

Normal Procedures 

Performance 

Weight & Balance/ 

Equipment List 

Airplane & Systems 

Descriptions 

Airplane Handling, 

Service & Maintenance 

Supplements 

Safety and Operational 

Tips (Optional) 

Alphabetical Index 

(OptioW 

Each section shall be complete within itself, with 

respect to page and numbering. There shall be a list 

of sections entitled "CONTENTS", in the front of 

the Handbook. 

0.33 Order and Numbering 

The order of presentation of the subject matter of the 

paragraphs used in this Specif~cation shall be 

followed in each Handbook except when 

(a) the inclusion of material called for in a 

paragraph is inappropriate for the type of 

airplane; or 

(b) the specific section indicates, under "General", 

that the order of presentation of the paragraphs 

is for guidance only and need not be followed. 

(See, for example, Section 7.1, General.) 

If a paragraph contains subparagraphs, the order of 

presentation of the subparagraphs is for guidance 

only and need not be followed. The Handbook 

producer should arrange the material within 

paragraphs in a manner he considers to be most 

informative to the kind of pilot expected to use the 

Handbook. 

The numbering of paragraphs and subparagraphs 

within a section is not required. If numbered they 

should be numbered sequentially and need not 

follow the numbering in this Specification so as to 

avoid "gaps" resulting from Specification material 

not appropriate to the type of airplane. 

0.35 Subject Headings 

Subject headings shall be the same as, or 

substantively equivalent to, the examples used in 

this Specification except when not appropriate 

because of the design or operational features of the 

type of airplane. 

0.41 Identifying Revised Material 

A revision to a page is defied as any change to the 

printed matter that was previously printed on that 

Page. 

Revisions, additions and deletions shall be identifled 

by a vertical black line along the outside of the page 

(or the gutter on two column pages) opposite only 

that portion of the printed matter that was changed. 

In the case of a revision to an illustration, a black 

vertical line will appear in the left margin opposite 

the revision. The date of the revision shall be shown 

on each revised page. (See Figure 0-2) 

0.43 Log of Revisions 

Each Handbook shall have a log of Revisions or 

effective pages, listing all revisions or effective 

pages, immediately following the Title Page. (Note: 

Do not print on the back of the title page.) 

Following the last entry, there shall be a box 

containing the date of the revision and the signature 

(over the printed name and title) of the person 

approving the revision. (See Figure 0-4) 

0.45 Obtaining Revisions 

The Handbook shall contain information concerning 

the procedures or actions that need to be taken by 

the operator of the airplane to maintain the 

Handbook in a current status. 

An appropriate warning or note shall be contained in 

each Handbook to inform the operator that a current 

Handbook is required to be in the airplane during 

flight and that it is the operator's responsibility to 

maintain the Handbook in a current status. 

0.51 Supplements 

Section 9 G' this Specification contains the 

requirements for supplements. 

0-4 

Q 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
Issued: February 15,1975 

Revised: October 18,1996 

PILOT'S OPERATING HANDBOOK 

AND 

FAA APPROVED AIRPLANE 

ELIGHT MANUAL 

THIS HANDBOOK INCLUES THE MATERIAL REWIRED 

TO BE FURNlSHW TO THE PLOT BY THE FEDERAL AVlA 

TlON REGULATIONS AND ADDITIONAL INFORMATION 

PROW BY THE MANUFACTURER, AW C013STmmS 

THE FAA APPROVED AIRPLANE RIGHT MANUAL. 

This Hmdbook meet8 GAMA Spodf krtion No. 1, SpecMcation tor Pilot's Operating Handbook, hued February 15, 

1975 end rwW.September 1. 1964. 

*pprowbd by the Federal Aviation Administration 

BY: 

(NAME) ~nn~) Manufacturers Nan# 

Figure 0-1 

Title Page Layout 

0 - 5 

-0 1996 General Aviation Manufacturers Association 
INTENTIONALLY LEFT BLANK 

0-6 

O 1996 General Aviation Manufacturers Association 

Issued: February 15, 1975 

Revised: October 18,1996 
ITEM DJMERUOIOS 

A 1" 

8 1R" 

C 1R" 

D 1R" 

E DI 

sppoer* 

Figure 0-2 

Suggested Vertical Page Layout 

Issued: February 15,1975 

Revised: October 18.1996 

0-7 

9 1996 General Aviation Manufacturers Association 
Tat cim 

NDBmkr 

Orlgh.lal issue or 

Date of Rarision 

C 

Figure 0-3 

Suggested Horizontal Page Layout 

0-8 

Q 1996 General Aviation Manufacturers Association 

Issued: Febtuary 15,1975 

Revised: October 18,1996 
PILOT'S OPERATlNG HANDBOOK 

LOG OF REVtSfONS 

Description of Revision 

Figure 0-4 

Suggested Log of Revisions 

I 

Page Number I 

Issued: February 15, 1975 

Revised: October 18,1996 

0 - 9 

Q 1996 General Aviation Manufacturers Association 
Page 

i saction Number 

I Ssction Tils I 

I 

0-10 

Q 1996 General Aviation Manufacturers Aacociation 

Figure 0-5 

Suggested Vertical Schematic 

issued: February 15,1975 

Revised: -bar 18,1996 
Layout 

Fire 0-6 

Fuel System Schematic 

Figure 0-6 

Fuel System Schematic 

Issued: February 15,1975 

Revised: Odober 18,1996 

0-11 

(O 1996 General Aviation Manufacturers Asaociation 

SECTION 1 

GENERAL 

TABLE OF CONTENTS 

paragraph Page 

General ............................................................................. 1-1 

Introduction .................................................................... 1 1 . Three View Drawings ....................................................... 1 . 1 

Required Descriptive Data ................................................ 1-1 

Engine(s) ........................................................................... 1 . 1 

Propeller(s) ....................................................................... 1-1 

Fuel ................................................................................... 1-1 

Oil ..................................................................................... 1-2 

Maximum CerMed Weights ............................................. 1-2 

Typical Airplane Weights ................................................. 1-2 

Cabin & Entry Dimensions ............................................... 1-2 

Baggage Space & Entry Dimensions ................................. 1-2 

Specific Loadings .............................................................. 1-2 

Symbols. Abbreviations & Terminology ........................... 1-2 

Conversion to Metric System ............................................ 1-6 

SECTION 1 

GENERAL 

General 

Section 1 of the Pilot's Operating Handbook shall 

present basic data and information of general interest 

to the pilot which is useful in loading, sheltering, 

handling, and routine preflight checking of the 

airplane. In addition, it shall provide defmitions or 

explanations of symbols, abbreviations, and 

terminology used in the Handbook. The selection of 

data by the Handbook producer, to be included in 

this Section shall be governed by the concepts 

contained in the Preface of this Specification. 

Introduction 

The introduction shall include a brief outline of the 

Handbook's content, organization, method of usage 

and the following statement: 

THIS HANDBOOK INCLUDES THE MATERIAL 

REQUIRED TO BE FURNISHED TO 'ITE PILOT 

BY THE FEDERAL AVIATION REGULATIONS 

AND ADDITIONAL INFORMATION PROVIDED 

BYTHEMANUFACmRANDCONS-S 

THE FAA APPROWD AIRPLANE FLIGHT 

MANUAL. 

Three View Drawing 

The airplane general arrangement shall be illustrated 

with a scale line drawing consisting of plan, side and 

front views presented in a vertical sequence upon a 

single page. Principal dimensions, particularly those 

useful for handling and sheltering the airplane, shall 

be shown upon the drawing. These dimensions 

include, as applicable: 

(a) Wing Span 

(b) Maximum Height 

(c) Overall Length 

(d) Wheel Base Length 

(e) Main Landing Gear Track Width 

(f) Maximum Propeller Diameter 

(g) Propeller Ground Clearance 

(h) Minimum Turning Radius 

(i) Wing Area 

Required Descriptive Data 

Descriptive Data shall be supplied for standard and 

optional engine and propeller installations and fuel 

and oil systems. The data may be supplemented by 

brief descriptions of additional characteristics or 

features if desired. The Handbook shall include the 

information outlined in paragraphs 1.13 through 

1.29, as applicable to the airplane. 

1.13 Engine(s) 

(a) Number of Engines 

(b) Engine Manufacturer 

(c) Engine Model Number 

(d) Engine Type, for Example: 

Reciprocating Engines 

Normally aspirated or Turbocharged 

Direct Drive or Geared 

Air or Liquid Cooled 

Horizontally Opposed or Radial 

Number of Cylinders 

Displacement 

Turbopropeller Engines 

Single Shaft or Multiple Shaft 

Compressor Stages and Types 

Combustion Chamber Type 

Turbine Stages and Type 

(e) Horsepower Ratings and Engine (or 

Propeller) Rotational Speed 

(1) Takeoff Power 

(2) Maximum Continuous Power 

(3) Maximum Normal Operating Power 

(4) Maximum Climb Power 

(5) Maximum Cruise Power 

Note: Horsepower ratings shall be in terms of 

horsepower for static, sea level. standard day 

conditions. 

1.15 Propeller(s) 

(a) Number of Propellers 

(b) Propeller Manufacturer 

(c) Propeller Model Number 

(d) Number of Blades 

(e) Propeller Diameter 

(f) Propeller Type. for Example: 

Fixed Pitch or Constant Speed 

Full Feathering 

Reversible 

Hydraulic or Electrically Actuated 

Pitch Range 

Issued: February 15, 1975 

Revised: October 18, 1996 

1-1 

Q 1996 General Aviation Manufacturers Association 
1.17 Fuel 

(a) Fuel Grade or Specification, (including color), 

alternate fuels and approved additives 

(b) Total Capacity 

(c) Usable Fuel 

1.19 Oil 

(a) Oil Grade or Specification 

(b) Viscosity Recommended for Various 

Average Air Temperature Ranges 

(c) Total Oil Capacity 

(d) Drain and Refill Quantity 

(e) Oil Quantity Operating Range 

1.21 Maximum Certificated Weights 

(a) Maximum Ramp Weight (if applicable) 

(b) Maximum Takeoff Weight 

(c) Maximum Landing Weight 

(d) Maximum Zero Fuel Weight (if applicable) 

(e) Maximum Weight@) in Baggage 

Compartment(s) 

1.23 Typical Airplane Weights 

Weights corresponding to the airplane as offered 

with typical seating and interior, avionics, 

accessories, standard equipment and fured ballast, 

and the typical empty weight and maximum useful 

load based on this weight. 

1.25 Cabin and Entry Dimensions 

(a) Cabin Width (Maximum) 

(b) Cabin Length (Maximum) 

(c) Cabin Height (Maximum) 

(d) Entry Width (Minimum) 

(e) Entry Height Wmmum) 

(f) Sill Height (Maximum) 

(g) Other dimensions useful in determining what 

may be loaded. 

1.27 Baggage Spaces and Entry Dimensions 

Baggage Space or Compartment 

(a) Compartment Width 

(b) Compartment Length 

(c) Compartment Height 

(d) Compartment Volume 

(e) Entry Width (Minimum) 

(f) Entry Height (Minimum) 

(g) Other dimensions useful in determining what 

may be loaded. 

1.29 Specific Loadings 

Wing and power loading, based on the Maximum 

Takeoff Weight of Paragraph 1.21(b) and the 

Takeoff Horsepower Rating of Paragraph 1. l3(e)(l) 

and the Wing Area of Paragraph 139. 

1.31 Symbols, Abbreviations and Terminology 

Define symbols, abbreviations and terminology 

necessary for the clear understanding and precise use 

of the information presented in various sections of 

the Handbook. Defmitions should emphasize 

operational significance when possible. 

The following guidelines shall be applied: 

1. Define all abbreviations used or referred to 

in the Handbook. 

2 Define any special terminologies used in 

the Handbook with emphasis on those 

which wuld be misused or misunderstood. 

3. Definitions should be worded as simply as 

possible and must conform with the use of 

the defined terms in the Handbook. 

4. Defmitions shall be consistent with 

definitions contained in the Federal 

Aviation Regulations. 

(a) General Airspeed Terminology and Symbols 

CAS 

KCAS 

GS 

IAS 

ms 

M 

TAS 

Calibrated Airspeed means the 

indicated speed of an aircraft, corrected 

for position and instrument error. 

Calibrated airspeed is equal to true 

airspeed in standard atmosphere at sea 

level. 

Calibrated Airspeed expressed in 

"knots". 

Ground Speed is the speed of an 

airplane relative to the ground. 

Indicated Airspeed is the speed of an 

aircraft as shown in the airspeed 

indicator when corrected for instrument 

error. IAS values published in this 

Handbook assume zero instrument 

error. 

Indicated Airspeed expressed in 

"knots". 

Mach Number is the ratio of true 

airspeed to the speed of sound. 

True Airspeed is the airspeed of an 

airplane relative to undisturbed air 

which is the CAS corrected for altitude, 

temperature and compressibility 

1-2 

O 1996 General Aviation Manufacturers Association 

Issued: February 15, 1975 

Revised: October 18,1996 
Maneuvering Speed is the maximum 

speed at which application of full 

available aerodynamic control will not 

overstress the airplane. 

Maximum Flap mended Speed is the 

highest speed permissible with wing 

flaps in a prescribed extended position. 

Mkrimum landing Gear Extended Speed 

is the maximum speed at which an 

aircraft can be safely flown with the 

landing gear extended. 

Maximum Landing Gear Operating 

Speed is the maximum speed at which 

the landing gear can be safely extended 

or retracted. 

Air Minimum Control Speed is the 

minimum flight speed at which the 

airplane is directionally and laterally 

controllable, determined in accordance 

with the Federal Aviation Regulations. 

Airplane certification conditions 

include one engine becoming 

inoperative and windmilling (or, in 

airplanes with autofeathering devices, 

feathered), not more than a 5" bank 

toward the operative engine, takeoff 

power on the operative engine, landing 

gear up, flaps in the takeoff position, 

and the most critical C.G. 

Maximum Operating Limit Speed is the 

speed limit that may not be deliberately 

exceeded in normal flight operations. V 

is expressed in knots and M in Mach 

Number 

Never Exceed Speed or Mach Number 

is the speed limit that may not be 

exceeded at any time. 

hhximum Structural Cruising Speed is 

the speed that should not be exceeded 

except in smooth air and then only with 

caution. 

Stalling Speed or the minimum steady 

flight speed at which the airplane is 

controllable. 

Stalling Speed or the minimum steady 

flight speed at which the airplane is 

controllable in the landing 

configuration. 

Intentional One Engine Inoperative 

Speed is the minimum speed, selected 

by the manufacturer, for intentionally 

rendering one engine inoperative, 

inflight, for pilot training. 

Note: Vs, is predicated upon the 

maintenance of conservative 

controllability margins when one engine 

is suddenly, intentionally rendered 

inoperative. Its selection shall be based 

upon the characteristics of the specific 

airplane to which it applies. However, 

in no case may it be lower than 1.05 

VMCA. 

Best Angle-of-Climb Speed is the 

airspeed which delivers the greatest 

gain of altitude in the shortest possible 

horizontal distance. 

Best Rate-of-Climb Speed is the 

airspeed which delivers the greatest 

gain in altitude in the shortest possible 

time. 

(b) Meteorological Terminology 

ISA International Standard Atmosphere in 

which 

(1) The air is a dry perfect gas; 

(2) The temperature at sea level is 15" 

Celsius (59" Fahrenheit); 

(3) The pressure at sea level is 29.92 

inches h g.(1013.2 mb); 

(4) The temperature gradient from sea 

level to the altitude at which the 

temperature is -56S°C ( -69.T) 

is - 0.00198°C ( - 0.003564°F) per 

foot and zero above that altitude. 

OAT Outside Air Temperature is the free air 

static temperature, obtained either Erom 

inflight temperature indications or 

ground meteorological sources, adjusted 

for instrument error and compressibility 

effects. 

Issued: February 15,1975 

Revised: October 18, 1996 

1-3 

Q 1996 General Aviation Manufacturers Association 
Indicated 

Pressure 

Altitude 

Pressure 

Altitude 

Station 

Pressure 

Wind 

The number actually read from an 

altimeter when the barometric subscale 

has been set to 29.92 inches of mercury 

(1013.2 mb). 

Altitude measured from standard sea 

level pressure (29.92 in. hg.) by a 

pressure or barometric altimeter. It is 

the indicated pressure altitude corrected 

for position and instrument error. In 

this Handbook, altimeter instrument 

errors are assumed to be zero. 

A@ atmospheric pressure at field 

elevation. 

The wind velocities recorded as 

variables on the charts of this Handbook 

are to be understood as the headwind or 

tailwind components of the reported 

wind. 

(c) Power Terminology 

Include, as applicable, the following defintions 

or explanations of terms. The definitions 

provided are examples. The defintions used in a 

particular Handbook should be appropriate for 

that particular airplane or installation. 

Takeoff 

Power 

Maximum 

Continuous 

Power (MCP) 

Maximum 

Continuous 

Power (MCP) 

Maximum 

Normal 

Opemting 

Power 

(MNOP) 

Cruising 

Climb 

Power 

Maximum 

Cruise 

power 

 he maximum power permissible 

for takeoff (may be time limited). 

(1) (for multi-engine aircraft) The 

maximum power for one 

engine inoperative, abnormal 

or emergency operations. 

(2) (for single-engine aircraft) 

Continuous The maximum 

power for abnormal or 

emergency operations. 

The maximum power for all 

normal operations (except 

takeoff). This power may be the 

same as Maximum Continuous 

Power. 

The power (not to exceed MNOP) 

recommended to operate the 

airplane in a cruise climb (a 

continuous, gradual climb) 

profile. 

The maximum power (not to 

MNOP) recommended for cruise 

Flight 

Idle 

Power 

Ground 

Idle 

Power 

Reverse 

Thrust 

Zero 

Thrust 

The power required to m an 

engine, in flight, at the lowest 

speed that will ensure satisfactory 

engine operation and airplane 

handling characteristics 

The power required to run an 

engine on the ground, as slowly as 

possible, yet sufficient to ensure 

satisfactory engine, engine 

accessory, and airplane operation 

with a minimum of thrust. 

The thrust of the propeller 

directed opposite the usual 

direction, thereby producing a 

braking action. 

The absence of appreciable thrust, 

in either direction. 

(d) Engine Controls and Instruments 

Include, as applicable, definitions, descriptions 

or explanations of the following terms or 

components. The defintions, descriptions and 

explanations provided are examples. Those used 

in a particular Handbook should be appropriate 

for that particular airplane or installation. 

Throttle 

or Power 

Control 

Lever 

Propeller 

Control 

Mixture 

Control 

The lever used to control engine 

power, from the lowest through the 

highest power, by controiling 

propeller pitch, fuel flow, engine 

speed, or any combination of these 

The lever used to select a propeller 

speed. For some airplanes, in the 

maximum decrease rpm position. it 

may feather the propeller. It may 

also activate the fuel cut off to that 

engine. 

On reciprocating (piston) engine 

powered airplanes, the mixture 

control provides a mechanical 

linkage with the mixture control 

valve of the carburetor, or the fuel 

control unit of fuel injection 

engines, to control the size of the 

fuel feed aperture, and thus, the 

aidfuel mixture. It is also a primary 

means to shut down the engine 

1-4 

Q 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
EGT 

Gauge 

Condition On some turbopropeller powered 

Lever airplanes, the condition lever is the 

primary control for starting and 

stopping the engine. On others, it is 

the primary control used to set 

engine and propeller speed. On 

some engines, it coordinates other 

power management system 

functions. It may also be used to 

feather or unfeather the propeller. 

The exhaust gas temperature 

indicator, on piston engine powered 

airplanes, is the imtmment used to 

identify the lea. fuel flow mixtures 

for various power settings. 

TIT, TI' A temperature measuring system 

or l'TI that senses gas temperature in the 

Gauge turbine section of the engine. On 

some engines, it indicates thrust or 

power. 

Tachometer An instrument that indicates 

rotational speed. On reciprocating 

engine installations, the speed is 

usually shown as propeller 

revolutions per minute (RPM). 

Turbine engine tachometers usually 

measure speed as a percentage of 

the nominal maximum speed of the 

turbine(s), unless specifically 

referred to the propeller 

Torquemeter An indicating system that displays 

the output torque available on the 

propeller shaft. Torque may be 

shown in dimensional terms, such as 

foot-pounds, or in reference terms, 

such as a percentage or a pressure. 

Propeller The device that regulates the rpm of 

Governor the engindpropeller by increasing 

or decreasing the propeller pitch, 

through a pitch change mechanism 

in the propeller hub. 

Beta On turbine powered aircraft using 

Range fully reversing propellers, this is the 

range of propeller blade angle 

movement not controlled by a 

governor and the propeller control 

lever. In this range, the blade pitch 

angle is scheduled by power lever 

movement and the constant 

propeller speed mechanism is 

blocked out. On some airplanes, a 

portion of the beta range may be 

used for drag control on approach, 

and on others, it is used only on the 

ground for taxi and reverse thrust 

control. 

(e) Airplane Per$ormance and Flight Planning 

Terminology 

Include definitions necessary for the pilot to use 

airplane performance information effectively. 

The following definitions should be included as 

applicable. 

Climb 

Gradient 

Demonstrated 

Crosswind 

Velocity 

AccelerateStop Distance 

AccelerateGo Distance 

The demonstrated ratio of the 

change in height during a portion of 

a climb, to the horizontal distance 

traversed in the same time interval 

The demonstrated crosswind 

velocity is the velocity of the 

crosswind component for which 

adequate control of the airplane 

during takeoff and landing was 

actually demonstrated during 

certification tests. The value shown 

may or may not be limiting. 

(Whether or not the value shown is 

limiting should be stated.) 

The distance required to accelerate 

an airplane to a specified speed and, 

assuming failure of an engine at the 

instant that speed is attained, to 

bring the airplane to a stop 

The distance required to accelerate 

an airplane to a specified speed an4 

assuming failure of an engine at the 

instant that speed is attained, 

continue take-off on the remaining 

engine(s) to a height of 50 feet. 

Issued: February 15, 1975 

Revised: October 18.1996 

1-5 

Q 1996 General Aviation Manufacturers Association 
MEA Minimum enroute IFR altitude. 

Route A part of a route. Each end of that 

Segment part is identified by: (1) a 

geographical location; or (2) a point 

at which a defmite radio fx can be 

established. 

(0 Weight and Balance 

Include defmitions of terms used in weight and 

balance descriptions and computations; such as: 

Reference 

Datum 

Station 

Arm 

Moment 

Center of 

Gravity 

(C.G.) 

C.G. Arm 

C . G. Limits 

An imaginary vertical plane 

from which all horizontal 

distances are measured for 

balance purposes. 

A location along the airplane 

fuselage usually given in terms 

of distance from the reference 

datum. 

The horizontal distance from the 

reference datum to the center of 

gravity (C.G.) of an item. 

The product of the weight of an 

item multiplied by its arm. 

(Moment divided by a constant 

is used to simplify balance 

calculations by reducing the 

number of digits.) 

The point at which an airplane 

would balance if suspended. Its 

distance from the reference 

datum is found by dividing the 

total moment by the total weight 

of the airplane. 

The arm obtained by adding the 

airplane's individual moments 

and dividing the sum by the total 

weight. 

The extreme center of gravity 

locations within which the 

airplane must be operated at a 

given weight 

Usable Fuel 

Unusable 

Fuel 

Standard 

Empty 

Weight 

Basic Empty 

Weight 

Payload 

Useful Load 

Maximum 

Ramp Weight 

Fuel available for flight 

planning. 

Fuel remaining after a runout 

test has been completed in 

accordance with governmental 

regulations. 

Weight of a standard airplane 

including unusable fuel, full 

operating fluids and full oil. 

Standard empty weight plus 

optional equipment. 

Weight of occupants, cargo and 

baggage. 

Difference between take off 

weight, or ramp weight if 

applicable, and basic empty 

weight. 

Maximum weight approved for 

ground maneuver. (It includes 

weight of start, taxi and run up 

fuel.) 

Maximum Maximum weight approved for 

Takeoff the start of the takeoff run. 

Weight 

Maximum Maximum weight approved for 

Landing the landing touchdown. 

Weight 

Maximum Maximum weight exclusive of 

Zero Fuel usable fuel 

Weight 

1.4 Conversion to Metric System 

At the option of the manufacturer, factors for 

conversion of dimensional, quantity and performance 

units to the metric system may be included. 

1-6 

8 1996 General Aviation Manufacturers Association 

Issued: February 15, 1975 

Revised: October 18,1996 
SECTION 2 

LIMITATIONS 

TABLE OF CONTENTS 

Page 

2-1 

meed Limitations ..................................................... 2-1 

Airspeed Indicator Markings ............................................. 2-3 

Power Plant Limitations (Reciprocating Engines) ............. 2-4 

Power Plant Limitations (Turbopropeller Engines) ............ 2-4 

Miscellanwus Instrument MarKings ................................. 2-5 

Weight Limits ................................................................... 2-5 

Center of Gravity Limits ................................................ 2-5 

Maneuver Limits ............................................................... 2-6 

Flight Load Factor Limits ................................................. 2-6 

Flight Crew Limits ............................................................ 2-6 

Kinds of Operations Limits ............................................... 2-6 

Fuel Limitations ............................................................ 2-6 

Climb Condition Limits ................................................. 2-6 

Maximum Operation Altitude Limit .................................. 2-6 

Outside Air Temperature Limit ......................................... 2-6 

Cabin Pressurization Limit ................................................ 2-6 

Maximum Passenger Seating Limit ................................... 2-6 

Systems & Equipment Limit ............................................. 2-6 

Other Limitations .............................................................. 2-6 

Placards ........................................................................... 2-6 

SECTION 2 

LIMITATIONS 

2.1 General 

This Section of the Pilot's Operating Handbook shall 

contain only those limitations required by regulation 

or necessary for safe operation of the airplane and 

approved by the regulatory authority. It shall present 

the various operating limitations, instrument 

markings, color coding and basic placards necessary 

for the safe operation of the airplane, its 

powexplant(s), systems and equipment. The content 

of this Section shall be guided by the following 

considerations: 

(a) As only approved limitations may be included in 

this Section, an introductory statement to this 

effect shall be contained in a prefatory note or 

the opening paragraph. For example: 

"The limitations included in this Section 

are approved by the Federal Aviation 

Administration. " 

(b) Limitations associated with optional systems or 

equipment may be included in this Section or in 

Section 9, Supplements. If limitations are 

incorporated in Section 9, this Section shall 

contain a note refening the reader to that section 

for limitations on the optional systems or 

equipment. 

issued: February 15,1975 

Revised: October 18, 1996 

(c) The specific content of this Section shall 

conform to the applicable Federal Aviation 

Regulations (FAR'S) governing the certification 

and operation of the particular airplane. Though 

this Section of this Specification often references 

Part 23 of the Federal Aviation Regulations 

(FAR 23), the references are for illustration 

purposes only. The applicable regulations for 

any specific airplane, which may differ from the 

referenced FAR, must be followed. 

Airspeed Limitations 

Provide airspeed limitations and the operational 

significance of such limitations. The name, symbol, 

value in knots, CAS, and LAS (assuming zero 

instrument error), and the significance of each 

airspeed, shall also be provided. Where the airspeed 

values may be applicable to more than one 

configuration, the more conservative IAS value shall 

be used. (See Figure 2-1) 

2-1 

Q 1996 General Aviation Manufacturers Associatiin 
I 

Maneuvering Speed 

VA (Knots) 

Maximum Flap 

Extended Speed 1 I 

vm (Know 

Maximum Landing Gear 

Operating Speed I I 

vm (Knots) 

Maximum Landing Gear 

Extended Speed I I 

v, (Know 

Air Minimum Control 

Speed 1 I 

v,, 

**Maximum Operating 

Speed Limit 

VMO (Knots) 

MMO Mach #) I 

*Never Exceed Speed I 

MNE (Mach #) 

*MaximumStructural 1 I 

MNO Wach #) 

Add any other speed limitations 

*reciprocating powered airplanes only 

** turbine powered airplanes only 

(Specify weight) 

Do not make full or abrupt control movements above this speed. 

(Specify flap setting) 

Do not exceed this speed with a given flap setting. 

Do not extend or retract landing gear above this speed 

Do not exceed this speed with landing gear ex%ended. 

This is the minimum flight speed at which the airplane is 

directionally and laterally controllable, determined in accordance 

with the Federal Aviation Regulations. 

Do not exceed this airspeed or Mach Number in any operation. 

Do not exceed this speed or Mach Number in any operation. 

Do not exceed this speed or Mach Number except in smooth air 

and then only with caution. 

Figure 2-1 

Airspeed Limitations 

Issued: February 1 5,1975 

O 1996 General Aviation Manufacturers Association Revised: October 18,1996 
2.5 Airspeed Indicator Markings 

An explanation of airspeed indicator markings, 

including the color coding, shall immediately follow 

the presentation on airspeed limitations. The use of 

line drawings or photographs to show the markings 

is encouraged. (See Figure 2-2) 

r Red Line 

I White Arc 

I Blue Line 

Yellow Arc 

Red Line 

Issued: February 15, 1975 

Revised: October 18,1996 

I I Full Flap Operating Range. Lower limit is maximum weight stalling speed I 

IAS VALUE OR RANGE 

I in landing configuration. Upper limit is maximum speed permissible with I 

SIGNIFICANCE 

Airspeed Control Speed (Multi-Engine Only) 

flaps extended 

One Engine Inoperative Best Rate of Climb (Specify Weight and Altitude if 

Applicable) 

Normal Operating Range. Lower Limit is maximum weight stalling speed 

I with flaps and landing gear (if retractable) retracted. Upper limit is I 

maximum structural cruising speed. 

Operations must be conducted with caution and only in smooth air. 

1 I Maximum speed for all operations I 

Figure 2-2 

Airspeed Indicator Markings 

2-3 

O 1996 General Aviation Manufacturem Association 
2.7 Power Plant Limitations (Reciprocating Engines) 

Provide the following powerplant limitations and 

data. as applicable: 

(a) Number of Engines 

(b) Engine Manufacturer 

(c) Engine Model Number 

(d) Engine Operating Limits for Takeoff Power, 

Maximum Continuous Power, and Maximum 

Normal Operating Power, as applicable. 

(e) Oil Pressure (Minimum and Maximum) 

(fl Fuel Pressure (Minimum and Maximum) 

(g) Other (Such as Ice Protection System Time 

Limit) 

(h) Fuel Grade or Specification. including color 

(i) Oil Grade or Spefication 

U) Number of Propellers 

(k) Propeller Manufacturer 

(I) Propeller Hub and Blade Model Numbers 

(m) Propeller Diameter (Minimum and Maximum) 

(n) Propeller Blade Angles at Specified Radius or 

Station 

(0) Propeller Operating Limits 

(l) Rotational Speed Restrictions 

Note: The Federal Aviation Regulations 

require the use of 'maximum continuous 

power", during certification of an airfiame 

and engine combination, to show 

compliance with certain standards. When 

the airplane manufacturer selects a 

"maximum continuous power less than the 

rated "maximum continuous power listed 

in the Engine Type Data Sheet. the 

maximum continuous power listed in the 

Airplane Type Data Sheet is used to show 

compliance with the applicable 

airworthiness standards and is the value 

shown in the Pilot's Operating Handbook. 

2.9 Powerplant Limitations (Turbine Engines) 

Provide the following powerplant limitations and 

data , as applicable: 

(a) Number of Engines 

(b) Engine Manufacturer 

(c) Engine Model Number 

(d) Engine Operating Limits shall be provided for 

the following applicable operations: 

(I) Takeoff 

(2) Maximum Continuous 

(3) Maximum Climb 

(4) Maximum Cruise 

(5) Normal Cruise 

(6) Idle (Flight andlor Ground) 

(7) Maximum Reverse 

(8) Acceleration 

(9) starting 

(10) Other 

(e) Operating Limits associated with the type of 

Operation specified by (d) above, may include: 

(I) Maximum Power Indication (Torque, Shaft 

Horsepower) 

(2) Maximum Shaft Rotational Speed 

(3) Maximum Gas Temperature 

(4) Maximum Time for Specified Operation 

(5) Maximum Oil Temperature 

(6) Other 

(f) Oil Pressure (Minimum and Maximum) 

(g) Fuel Pressure (Minimum and Maximum) 

(h) Other (Such as Generator or Alternator Limits) 

(i) Fuel Grade or Specification and Approved Fuel 

Additives (Preferred and alternate, with any 

Limitations on use of Aviation Gasoline) 

(j) Oil Grade or Specification and Approved Oil 

Additives 

(k) Number of Propellers 

(1) Propeller Manufacturer 

(m) Propeller Hub and Blade Model Numbers 

(n) Propeller Diameter (Minimum and Maximum) 

(0) Propeller Blade Angles and Specified Radius or 

Station 

@) Propeller Operating Limits 

(l) Rotational Speed Restrictions 

2-4 

Q 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18, 1996 
2.11 Powerplant Instrument Markings powerplant limitations. The use of line drawings or 

An explanation of powerplant instrument markings photographs to show the markings is encouraged. 

shall immediately follow the presentation on (See Figure 2-3.) 

I INSTRUMENT I Red Line I yellow I Green Arc I Yellow Arc 1 Red Line I 

POWER INDICATOR 

TACHOJs4ETER 

MANIFOLD PRESSURE 

GAS TEMPERATURE 

OIL TEMPERATURE 

CYLINDER HEAD TEMPERATURE 

COOLANT TEMPERATURE 

FUEL PRESSURE 

I OK PRESSURE I I I I I 1 

LIMIT 

- - I OTHER (As Generator) I 

I I I I 

Figure 2-3 

Power Plant Instrument Markings 

Arc 

CAUTIO 

N 

RANGE 

2.12 Miscellaneous Instrument Markings 

Provide limitations and markings for miscellaneous 

instruments, such as a pneumatic pressure gauge or a 

vacuum/pressure instrument gauge, as appropriate. 

2.13 Weight Limits 

Maximum Certificated Airplane Weights shall be 

started as required. If appropriate, reference shall be 

made to data in Section 5 (Performance) of the 

Pilot's Operating Handbook concerning the 

Maximum Takeoff Weight as limited by 

performance. If certif~cated in more than one 

category, the weights, with any restrictions, shall be 

given for each category. The following weights shall 

be presented if applicable: 

(a) Maximum Ramp Weight 

(b) Maximum Takeof Weight 

(c) Maximum Landing Weight 

(d) Mmimum Zero Weight 

(e)Mmcimum Weight($ in Baggage 

Compartment(s) 

NORMAL 

OPERATIN 

G 

2.15 Center of Gravity Limits 

Allowable Forward and Aft Center of Gravity Limits 

shall be presented as required. These limits shall be 

presented for each Category for which the aircraft is 

certificated. These limits shall be specified over the 

range from Minimum to Maximum Takeoff Weight, 

landing gear extended, and shall include the 

following supporting information: 

(a) Guidance as to the proper method of 

interpolating tabular statements of the center of 

gravity limits for various weights 

(b) A definition of the Reference Datum relative to 

the airfr-ame in terms convenient for operational 

use 

(c) The length and location of the leading edge of 

the Mean Aerodynamic Cord, if used 

(d) If removable ballast is used, the location and 

amount of the ballast weight, and any 

cautionq information required 

Issued: February 15, 1975 

Revised: October 18,1996 

CAUTION OR 

TAKEOFF 

2-5 

8 1996 General Aviation Manufacturers Association 

MAXIMUM 

LIMIT 
2.17 Maneuver Limits 

The following information on maneuvers 

appropriate to the Airplane Category shall be given: 

(a) A Statement of Authorized Maneuvers and 

Appropriate Entry Speeds 

(b) A Statement of Unauthorized Maneuvers 

(c) A Statement that the airplane is Approved for 

Spins, Unapproved for Spins, or is characteristically 

incapable of spinning 

2.19 Flight Load Factor Limits 

The limit manewering load factors, in g units of 

acceleration, for clean cruise and landing 

configurations, shall be given. The negative g limit, 

flaps up, should be given for aircraft approved for 

spinning or aerobatics. 

2.21 Flight Crew Limits 

Provide a statement of the minimum crew and the 

function of each flight crew member, if more than 

one is required. 

2.23 Kinds of Operations 

Provide, at an appropriate place in this Section, a 

statement of the kinds of operations allowed when 

listed operable equipment is installed. If any 

installed equipment affects an operating limitation, 

the equipment shall be listed and identified as to 

operational function. 

2.25 Fuel Limitations 

Total capacity and usable fuel shall be stated and, if 

the unusable fuel exceeds the limits of FAR 23, 

information shall be given idenwing the quantities 

unusable in flight. 

2.27 Climb Condition Limits 

For turbopropeller powered airplanes only, the 

established temperatures and corresponding altitude 

limits of powerplant components and engine fluids 

shall be stated. 

2.29 Maximum Operating Altitude Limit 

For pressurized airplanes and turbosupercharged or 

turbopropeller powered airplanes, the Maximum 

Altitude Limits shall be stated. 

2.31 Outside Air Temperature Limits 

For turbopropeller powered airplanes only, the 

Minimum and Maximum Outside Air Temperature 

Limits shall be presented as a function of pressure 

altitude. 

2.33 Cabin Pressurization Limit 

Data shall be presented stating the Normal and 

Maximum Cabin Operating Differential Pressure. 

Restrictions on use of cabin pressurization during 

takeoff, landing, or in flight shall be noted, if 

applicable. 

2.35 Maximum Passenger Seating Limits 

Any limits on Maximum Passenger Seating, by 

number of passengers or specific restrictions on seat 

occupancy, shall be stated. 

2.37 Systems and Equipment Limits 

Limits on any Airplane systems or equipment shall 

be provided. For example, limits may be necessary 

in connection with electrothermal elements used in 

ice protection systems, or in battery temperatures. 

Provide limitations necessary for the safe operation 

of optional systems or equipment in this Section or 

in Section 9, Supplements, or in both. 

2.39 Other Limitations 

Provide a statement of any limitation required by 

regulation or permitted or approved by the 

regulatory authority, not specifically covered in this 

Section. 

2.41 Placards 

Operating Placards shall be listed or illustrated. 

2 - 6 

O 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
SECTION 3 

EMERGENCY PROCEDURES 

TABLE OF CONTENTS 

Paragraph Page 

3.1 General ............................................................................ 3-1 

3.3 Airspeeds for Emergency Operations ................................ 3-1 

3.5 Emergency Procedures Check List .................................... 3-1 

3.7 Amplified Emergency Procedures ..................................... 3-1 

3.9 Emergencies ..................................................................... 3-2 

a . Engine Failure ........................................................... 3-2 

b . Air Start ..................................................................... 3-2 

c . Smoke and Fire' ......................................................... 3-2 

d . Emergency Descent ................................................... 3-2 

e . Glide .......................................................................... 3-2 

f . Landing Emergencies ................................................ 3-2 

g . System Emergencies .................................................. 3--1 

h . Spin ........................................................................... 3-2 

i . Other 3-3 

SECTION 3 

EMERGENCY PROCEDURES 

3.1 General 

This Section of the Pilot's Operating Handbook sW 

clearly and precisely describe the recommended 

procedures for coping with various types of 

emergencies or critical situations. Procedures for 

handling malfunctions or other abnormalities that are 

not of emergency nature, or involve a potential 

emergency that may be deferred. may be included in 

this Section or in optional Section 34 Abnormal 

Procedures. The incorporation of an Abnormal 

Procedures Section in Handbooks is encouraged. 

The subject matter and subject headings of this 

Section of a Handbook shall conform to the order 

and headings of paragraphs in this Section of the 

Specification. 

The material within subparagraphs of a Handbook 

may follow the order of material within 

subparagraphs of this section of the Specification or 

may be arranged to suit a particular type or model of 

airplane. In addition, Handbook writers shall 

consider the following objectives: 

(a) Airspeeds used in the Emergency Procedures 

shall be specified in terms of Indicated Airspeed, 

assuming zero instrument error. in order to make 

the information as directly usable as possible. 

(b) The Emergency Procedures Section shall include 

at the beginning a check list with regard to order 

of action when sequence is essential to safety. 

(c) The check list may be followed by amplified 

procedures to provide pilots with a better 

understanding of the reasons for actions in the 

short form check list. 

(d) Emergency procedures associated with optional 

systems or equipment may be included in this 

Section or in Section 9, Supplements. If 

emergency procedures are incorporated in 

Section 9, this Section shall contain a note 

referring the reader to that Section for 

emergency procedures on the optional systems 

or equipment. 

3.3 Airspeeds for Emergency Operations 

(a) Required and recommended airspeeds (and the 

configuration of the airplane for which the 

airspeeds apply) deemed likely to enhance safety 

of operation during an emergency shall be listed 

near the beginning of this Section or in the 

Emergency Procedures Check List, or both. For 

example. this list will include speeds such as the 

manewering airspeed(s) and the speed(s) for 

maximum gliding distance. 

(b) In addition, for multi-engine airplanes, include 

the one engine inoperative best rate of climb 

speed ('VY&, the one engine inoperative best 

angle of climb speed (Vx&, and the air 

minimum control speed (VMCA) with the critical 

engine inoperative. For these speeds, provide the 

signifkant conditions under which they may be 

obtained (aircraft weighty, atmospheric 

conditions, etc.). 

3.5 Emergency Procedures Check List 

The emergency procedures check list should be in 

concise, abbreviated form designed to remind pilots 

of items to check without providing details 

concerning the opmtion of any system. 

The check list may be arranged by 'Challenge" 

and "Response" headings for two pilot aircraft or by 

"Item" and "Condition" headings for single pilot 

aircraft. Under either method, the item to be checked 

is listed with the desired condition stated. Key words 

or switch and lever positions are capitalized in the 

Condition Column. 

EXAMPLE: 

CHALLENGE OR RESPONSE OR 

ITEM CONDITION 

Battery Switch OFF 

Generator OFF 

The check list should be limited to the minimum 

number of items determined to be essential to aid the 

pilot in an emergency. 

3.7 Amplified Emergency Procedures 

The check list may be followed by additional 

information (amplified procedures) to provide pilots 

with a better understanding of the reasons for actions 

in the check list. The amplified procedures may also 

Issued: February 15.1975 

Revised: October 18,1996 

3-1 

Q 1996 General Aviation Manufacturers Association 
include additional procedures that a pilot would not 

reasonably be expected to refer to in resolving a 

given emergency. Discussion of emergency 

situations, the resolution of which are not amenable 

to check list format, may also be included. 

3.9 Emergencies 

3,9(a) Engine Failure 

Procedures shall be provided for all airplanes for all 

cases of engine failure, including partial failure 

(partial power), during takeoff and in flight 

3.9(b) Air Start 

Procedures shall be provided for starting the engine 

in flight and, in the event the engine does not start, 

for subsequent action(s). 

3.9(c) Smoke and Fire 

Procedures shall be provided for coping with cases of 

smoke and/or fire in the cabin or from an engine in 

the following flight phases: 

(1) On the Ground 

(2) During Takeoff 

(3) In-Flight 

3,9(d) Emergency Descent 

Procedures shall be provided for making an 

emergency descent. 

3.9(e) Glide 

Procedures and information shall be provided for a 

gliding descent. including: 

(1) The Recommended Airspeed 

(2) The Associated Configuration 

(3) The distance(s) from (a) specified height(s) 

above ground level that an airplane will glide, or 

the glide ratio in nautical miles per thousand 

feet. 

3.90 Landing Emergencies 

Procedures shall be provided for the various landing 

emergencies, including: 

(1) For all airplanes, forced landings under the 

following conditions: 

(A) Precautionary Landings 

(B) With a Flat Tire 

(C) With a Defective Landing Gear 

@) With Power, Landing Gear Retracted 

@) Without Power, Landing Gear Retracted 

O Ditching, for aircraft with extended 

overwater flight capability 

(G) Approach and landings with flaps retracted, 

if flapless landings require any special 

technique or if information is required by 

the certificating authority. 

(2) For Multi-Engine Airplanes Only: 

(A) One Engine Inoperative Landing 

(B) One Engine Inoperative Go-Around 

(If this maneuver cannot be performed 

safely, a warning against attempting it shall 

be provided.) 

3.9(g) System Emergencies 

Procedures shall be provided for coping with 

emergencies involving the following systems, as 

applicable: 

(1) Engine 

(2) Superchargerlturbocharger or other 

augmentation 

(3) Propeller 

(4) Fuel 

(5) Electrical 

(6) Hydraulic 

(7) Pneumatic 

(8) Flight Controls 

(9) Landing Gear 

(10) Nose Wheel Steering 

(1 1) Environmental 

(12) Oxygen 

(13)Ice Protection 

(14) Emergency Exits 

(15)0ther 

3.9(h) Spins 

Handbooks for all single engine airplanes, other than 

for those airplanes which have been shown to be 

"characteristically incapable of spinning" shall 

contain procedures for recovery from spins. These 

procedures shall be in the Emergency Procedures 

Section for all airplanes except those in the acrobatic 

category. Spin recovery procedures for acrobatic 

airplanes may be included under Normal Procedures. 

If the airplane has not been tested for spin 

characteristics and recovery methods, a discussion of 

prevention of spins and probable best recovery 

techniques will be included with the qualification 

that no tests were made and the recovery techniques 

are based on the best judgment of the manufacturer. 

3 - 2 

O 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
Spin recovery procedures for multi-engine airplanes 3.9(i) Other 

may be included at the option of the manufacturer. It Emergency Procedures and other pertinent 

should be noted that multi-engine airplanes have not information necessary for safe operations shall be 

been spun by the manufacturer, if such is the case. provided for emergencies peculiar to a particular 

airplane design, operating or handliig characteristics 

Issued: February 15, 1975 

Revised: October 18,1996 

3-3 

Q 1996 General Aviation Manufacturers Association 

SECTION 3A 

ABNORMAL PROCEDURES 

TABLE OF CONTENTS 

Paragraph Page 

3A.1 General .......................................................................... 3A-1 

3A.3 Airspeeds for Abnormal Operations ............................... 3A-1 

3A.5 Abnormal Procedures Check List ................................... 3A-1 

3A.7 Amplified Abnormal Procedures .................................... 3A-2 

3A.9 Abnormalities ................................................................ 3A-2 

SECTION 3A 

ABNORMAL PROCEDURES 

3k 1 General 

This section of the Pilot's Operating Handbook shall 

clearly and precisely describe the recommended 

procedures for handling malfunctions of equipment, 

or other abnormalities, that are not of an emergency 

nature or involve a potential emergency that may be 

deferred. An example of a deferred emergency is a 

landing gear that does not respond properly to 

normal gear switch actions when there are no other 

malfunctions in the powerplant or other systems. A 

gear up emergency landing, if necessary can be 

deferred until after all other methods of lowering the 

gear have been unsuccessfully tried and a suitable 

landing area has been selected. Examples of less 

critical abnormal conditions include failure of some 

portion of the electrical system in day VFR 

conditions, failure of automatic pilots or wing 

levelers enroute, or failure of some, but not all 

elements of the navigation and communication 

systems. 

An "emergency" however, almost always involves a 

failure that requires immediate and rapid response, 

such as a total powerplant failure, fire or smoke, or 

rapid cabin decompression. The difference between 

an "emergency" and "abnormal" situation may also 

depend on the circumstances of flight, i.e., night or 

IFR versus day VFR, the presence of icing 

conditions, or the occurrence of multiple 

malfunctions. 

Because differences in design and complexity of the 

various types and models of airplanes play a major 

role in deciding whether a specific malfunction is 

more appropriately listed under "emergency" or 

"abnormal" procedures, or whether an "Abnormal 

Procedures" section is desirable, the decision to 

include an "ABNORMAL PROCEDURES" Section, 

or provide only an "EMERGENCY PROCEDURES" 

Section, is left to the Handbook producer. 

If an Abnormal Procedures Section is provided, the 

subject matter and subject headings of this Section of 

a Handbook shall conform to the order and headings 

of paragraphs in this Section of the Specification. 

The material within subparagraphs of a Handbook 

may follow the order of material within 

subparagraphs of this Section of the Specification or 

may be arranged to suit a particular type or model of 

airplane. In addition, Handbook writers shall 

consider the following objectives: 

(a) Airspeeds used in this Section shall be specified 

in Indicated Airspeed, assuming zero instrument 

error, in order to make the information as 

directly usable as possible. 

(b) The Abnormal Procedures Section shall include, 

at the beginning, a check list with regard to 

order of action when sequence is essential to 

safety. 

(c) The Check List may be followed by amplified 

procedures to provide pilots with a better 

understanding of the reasons for actions in the 

check list. 

(d) Abnormal procedures associated with optional 

systems or equipment may be included in this 

Section or in Section 9, Supplements. If 

Abnormal Procedures are incorporated in 

Section 9, this Section shall contain a note referring the reader to that Section for abnormal 

procedures on the optional systems or 

equipment. 

(e) The exact content of the Abnormal Procedures 

Section shall be determined by each Handbook 

producer, considering the design features of each 

airplane. 

3k 3 Airspeeds for Abnormal Operations 

Airspeeds (and the configuration of the airplane for 

which the airspeeds apply) deemed likely to enhance 

safety of operation during an abnormal situation shall 

be listed near the beginning of this Section or in the 

Abnormal Procedures Check List. or both. 

3k5 Abnormal Procedures Check List 

The Abnormal Procedures Check List should be in 

concise, abbreviated form and designed to remind 

pilots of items to check without providing details 

concerning the operation of any system. The Check 

List may be arranged by "Challenge" and "Response" 

headings for two pilot aircraft or by "Item" and 

"Condition" headings for single pilot airrraft. Under 

either method, the item to be checked is listed with 

the desired condition stated. Key words or switch and 

Issued: February 15, 1975 

Revised: October 18, 1996 

3A-1 

6 1996 General Aviation Manufacturers Association 
lever positions are capitaiized in the Condition 

column. 

EXAMPLE: 

CHALLENGE OR RESPONSE OR 

IlTM CONDITION 

Gear Selector UP 

Generator Trip 

Switches PUSH 

3A.7 Amplified Abnormal Procedures 

The Check List may be followed by additional 

information (amplified procedures) to provide pilots 

with a better understanding of the reasons for actions 

in the Check List. In addition, or as an alternative, 

there may be a reference to Section 7, Description of 

the airplane and Its System or Section 9, 

Supplements. 

3A-2 

0 1996 General Aviation Manufacturerr Association 

3k9 Abnormalities 

The abnormalities to be included in this Section shall 

be determined by the Handbook producer, 

considering the following: 

(a) Engine 

(b) propeller 

(c) Fuel 

(d) Electrical 

(e) Hydraulic 

(f) Pneumatic 

(g) Flight Controls 

(h) Landing Gear 

(I) Nose Wheel Steering 

(j) Environmental 

(k) Oxygen 

(l) Ice Protection 

(m) Emergency Exits 

(n) other 

Issued: February 15,1975 

Revised: October 18, 1996 
SECTION 4 

NORMAL PROCEDURES 

TABLE OF CONTENTS 

Paragraph Page 

4.1 General ............................................................................. 4-1 

4.3 Airspeeds for Nonnal Operation ........................................ 4-1 

4.5 Normal Procedures Check List .......................................... 4-1 

4.7 Amplified Normal Procedures .......................................... 4-1 

4.9 Normal Procedures ............................................................ 4-2 

Preflight Inspection ................................................... 4-2 

Before Engine Starting ............................................... 4-2 

Use of External Power ................................................ 4-2 

Engine Starting ........................................................... 4-2 

Before Taxiing ........................................................... 4-2 

Taxiing ....................................................................... 4-2 

Before Takeoff ........................................................... 4-2 

Takeoff ...................................................................... 4-2 

Climb ........................................................................ 4-2 

Cruise ....................................................................... 4-2 

Descent ...................................................................... 4-2 

Before Landing .......................................................... 4-2 

Balked Landing .......................................................... 4-2 

Mer Landing ............................................................ 4-2 

Shutdown ................................................................. 4-2 

Postflight . ELT ......................................................... 4-2 

4.1 1 Environment Systems ........................................................ 4-2 

4.13 Other Normal Procedures .................................................. 4.2 

4.15 Noise Characteristics ......................................................... 4-2 

4.17 Procedures for Practice Demonstration of V,,, ................ 4-2 

4.19 Fuel Conservation ............................................................ 4-2 

SECTION 4 

NORMAL PROCEDURES 

4.1 General 

This Section of the Pilot's Operating Handbook shall 

clearly and precisely describe the recommended 

procedures for the conduct of normal operations. 

Except as noted in paragraph 4.19, the subject matter 

and subject headings of this Section of the Handbook 

shall conform to the order and headings of 

paragraphs in this Section of the Specification. 

The material within subparagraphs of Handbooks 

may follow the order of material within 

subparagraphs of this Section of the Specification or 

may be arranged to suit a particular type or model of 

airplane. In addition, Handbook writers shall 

consider the following objectives: 

(a) Airspeeds used in this Section shall be specified 

in Indicated Airspeed, assuming zero instrument 

error, in order to make the information as 

directly usable as possible. 

(b) The Normal Procedures Section shall include, at 

the beginning. a check list, with regard to order 

of action, when sequence is essential. 

(c) The Check List may be followed by amplified 

procedures to provide pilots with more detail on, 

and better understanding of, the reasons for 

actions in the Check List. 

(d) Normal procedures associated with optional 

systems or equipment may be included in this 

Section or in Section 9, Supplements. If normal 

procedures are incorporated in Section 9, this 

Section shall contain a note referring the reader 

to that Section for normal procedures on the 

optional systems or equipment. 

(e) The exact content of the Normal Procedures 

Section shall be determined by the applicable 

regulations of the certif~cating authority and by 

the operating and design features of each 

particular airplane. AU information required by 

FAR Part 23, or other applicable regulations, 

will be included. 

4.3 Airspeeds for Normal Operations 

The airspeeds which may enhance the safety of 

operations shall be provided as a preface to the 

Normal Procedures Section. The following speeds, 

with associated weight, atmospheric and other 

conditions, shall be given: 

(a) The ALL Engines Recommended Climb Speed 

(b) The ALL Engines Best Angle of Climb Speed 

(c) ALL Engines Approach Speed 

(d) Speeds for Transition to the Balked Landing 

Condition 

(e) The Maximum Demonstrated Crosswind 

Velocity 

(fl The Recommended Turbulent Air Penetration 

Speed 

(g) Other airspeeds recommended by the 

manufacturer, such as Intentional One Engine 

Inoperative Speed. 

4.5 Normal Procedures Check List 

The normal procedures check list should be in 

concise, abbreviated form and designed to remind 

pilots of items to check without providing details 

concerning the operation of any system. 

The Check List may be arranged by "Challenge" and 

"Response" headings for two pilot airplanes or by 

"Item" and "Condition" headings for single pilot 

airplanes. Under either method, the item to be 

checked is listed with the desired condition stated. 

Key words or switch and lever positions are 

capitalized in the Condition Column. 

EXAMPLE: 

CHALLENGE OR RESPONSE OR 

ITEM CONDITION 

Mixture RICH 

Generators ONfCHECKED 

Carburetor Heat COLD 

The Check List may also contain supplemental 

information pertinent to the operation of the airplane, 

such as performance data, optional equipment 

operation, etc., that the pilot might routinely use. 

4.7 Amplified Normal Procedures 

Additional information, to provide a more complete 

understanding of the items in the Normal Procedures 

Check List, in the order of this Check List. may be 

included in this Section immediately following the 

Check List. The Amplified Normal Procedures are 

not intended for routine use in flight, permitting 

substantial detail and explanation. For example, if 

the Check List lists "engine run-up", the amplified 

Issued: February 15, 1975 

Revised: October 18, 1996 

4-1 

O 1996 General Aviation Manufacturers Association 
procedures would explain how to perform the run-up. Section may also include normal procedures for 

Items essential or pertinent to the operation of the features peculiar to a particular airplane design or to 

airplane not included in the Check List may also be particular handling characteristics. For example, spin 

included in this Section following the infonnation on recovery techniques may be included in this Section 

items in the Check List. of an acrobatic category airplane Handbook. 

4.9 Normal Procedures 

Except when inapplicable or inappropriate to the 

particular airplane model, Handbooks shall contain 

the recommended normal procedures for the 

following phases of flight, in the order shown. 

(a) Preflight Inspection 

(b) Before Engine Starting 

(c) Use of Extd Power 

(d) Engine Starting 

(e) Before Taxiing 

(0 Taxiing 

(g) Before Takeoff 

(h) Takeoff 

- Normal 

- Short Field* 

- Soft Field* 

(i) Climb 

(i) Cruise 

(k) Descent 

(1) Before Landing 

(m) Landing 

- Normal 

- Short Field* 

- Soft Field* 

- Balked 

(n) After Landing 

(0) Shutdown 

@) Postflight ELT 

* Where such operations are approved 

4.11 Environmental Systems 

Include information necessary for safe operation of 

(a) Oxygen Systems (include capacity and duration) 

@) Pressurization System 

(c) Heating & Ventilating Systems 

(d) Air Conditioning Systems 

4-13 Other Normal Procedures 

Other procedures essential or pertinent to the 

operation of the airplane may be included in the 

Handbook. Generally, this will include information 

based on the standard or typical airplane and its 

systems and equipment. Information on specific 

optional systems or equipment may be included in 

this Section or in Section 9, Supplements. This 

4.15 Noise Characteristics 

In addition to information required by Part 36 of the 

Federal Aviation Regulations, the Handbook 

producer shall provide strongly worded advice to be I 

used by the operator to minimize the noise impact of 

the airplane during operation at, or in the vicinity of, 

airports. 

4.17 Procedures for Practice Demonstration of V,, 

For multi-engine airplanes, procedures shall be 

provided for practice demonstrations of VMm. The 

procedures shall be based on the use of V, 

Intentional One Engine Inoperative Speed. 

The procedure shall specify that intentionally 

rendering one engine inoperative for the purpose of 

demonstrating, or training in, the recognition of 

VMcA will be done by starting at or above Vs, then 

gradually reducing the speed (at approximately one 

knot per second) until either VMcA or stall warning, 

I whichever occurs first, is obtained. 

Some types of airplanes (e. g., turbopropeller 

powered) may have VMcA determined with automatic 

propeller pitch control devices that may have 

substantially more drag from an engine operating at 

reduced power, to simulate an engine failure, than 

I with an inoperative engine. In such cases (where 

V, is established at a speed to accommodate 

simulated engine failure by power reduction) the 

procedures shall include an explanation of the 

difference between simulated and actual power loss. 

There should be a note that V, is used only in 

training and is not a limiting speed. 

4.19 Fuel Conservation 

(a) Recommended fuel conservation procedures, 

appropriate to all phases of ground and flight 

operations, considering engine cooling, 

performance, and economy, shall be integrated 

into this Section (an4 as appropriate, in Section 

5, Performance). The main objective is to show 

how to maximize ground (nautical) miles per 

gallon (pound) by careful flight planning and 

4-2 

O 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
attention to good operating procedures. The 

information may be expressed in discussing 

examples, graphs, tables or other means, or any 

combination thereof. In addition, general 

information and tips on fuel conservation may be 

included in Section 10 of the Handbook (if 

incorporated). 

(b) The information shall include a discussion of the 

effects of variables (such as leaning and power 

settings, wind components, air temperature, 

cruise speeds, altitudes and weight) on fuel 

consumption. The significant tradeoffs to be 

considered in order to obtain the best fuel 

economy must be explained. 

(cj The recommended fuel consemation procedures 

shall contain a caution, if applicable, that the 

power settings recommended by the 

manufacturer must be used during the break-in 

period of new and newly overhauled engines. 

The use of economy power settings during this 

period may be detrimental to the engine life. 

Issued: February 15, 1975 

Revised: October 18, 1996 

4-3 

Q 1996 General Aviation Manufacturers Association 

SECTION 5 

PERFORMANCE 

TABLE OF CONTENTS 

Paragraph Page 

General .................................................................................. 

Fuel Conservation Information ............................................... 

Identification of Graphs & Tables .......................................... 

Limitations ............................................................................. 

Format Options ...................................................................... 

ReaWiity of Graphs ............................................................ 

Readability of Tables ............................................................. 

Associated Conditions ............................................................ 

Technique .............................................................................. 

Examples ............................................................................... 

Location of Examples . Associated Conditions and Technique 

Weight ................................................................................... 

Airspeeds ............................................................................... 

Distances ................................................................................ 

Pressure Altitude & Air Temperature ..................................... 

Wind Velocities ..................................................................... 

Fuel Density ........................................................................... 

Performance Formats & Rules ................................................ 

Minimum Performance Presentations for Single Engine 

Aircraft ............................................................................... 

Minimum Performance Presentations for Multi-Engine 

Aircraft ............................................................................... 

Performances Presentations in Icing Conditions ..................... 

List of Figures ........................................................................ 

SECTION 5 

PERFORMANCE 

5.1 General 

(a) This Section of the Pilot's Operating Handbook 

shall contain all performance information 

required by the Federal Aviation Regulations (or 

other applicable regulations) and this 

Specification. Additional performance and 

related information may be provided to enhance 

the pilot's operation of the airplane. The basis for 

such information may be stated (e . g., 

calculations, tests, analysis based on similar 

designs. etc.) 

(b) The subject matter, including optional 

information, of this Section of the Handbook 

shall conform to the following general order of 

presentation unless a different order is more 

suitable for a particular airplane: 

(1) Introduction, general information, and 

sample flight planning calculations. 

(2) Takeoff. 

(3) Climb. 

(4) Cruise. 

(5) Descent. 

(6) Landing. 

(c) Paragraphs 5.37 and 5.41 set forth the detailed, 

minimum subject matter and typical order of 

presentation within each phase of operation (or 

subject) listed in subparagraph (b) of this 

paragraph. Additional information provided by 

the manufacturer should be appropriately 

integrated into the order shown in paragraphs 

5.37 or 5.4 1. Figures 5-29 and 5-30 are examples 

of orders of presentation in which optional items 

have been incorporated. 

5.3 Fuel Conservation Information 

Recommended Fuel Conservation Information shall 

be integrated into this Section to show the pilot how 

to minimize fuel usage during operation of the 

airplane. 

5.5 Identification of Graphs or Tables 

For standardization and user convenience, the titles 

in the "LIST OF FIGURES" on page 5-7 should be 

used to identify the appropriate items of airplane 

performance. Where two or more graphs or tables, 

which are similar in appearance, are used to cover 

the variation of items. such as alternative takeoff 

wing flap settings, the title information should be 

amplified as required to insure immediate 

recognition of the particular case. 

5.7 Limitations 

Limitations contained in this Section shall be clearly 

noted and mss-referenced to the appropriate 

paragraph in Section 2 of the Handbook. 

5.9 Format Options 

Airplane performance data shall be presented in 

either graphical or tabular formats. 

5.11 Readability of Graphs 

For graphical data presentations, the incremental 

value of the smallest graduation or pair of reticle 

lines should be the product of 1, 2, or 5, multiplied 

by an integral power of 10. 

5.13 Readabity of Tables 

For tabular data presentations, independent variables 

shall be chosen so that hear interpolation of the data 

will provide a reasonable approximation of the 

function value to be extracted. 

When other than simple interpolations in tables are 

involved, such as three way interpolations, 

explanations and examples of interpolation shall be 

included or a procedure for selecting conservative 

approximations may be given. This may be done in 

the Sample Flight Planning Section or on the specific 

table. 

5.15 Associated Conditions 

Each item of Airplane Performance shall include a 

statement of significant conditions associated with 

the data. As a minimum, the following information 

shall be provided as applicable. 

(a) Power Setting and Propeller Condition 

Note: Whenever a Maximum Normal Operating 

Power (MNOP) is included as a limitation, it 

may not be shown to be exceeded on any chart 

except those concerning takeoff, emergency, or 

abnormal procedures. 

(b) wing Flaps 

(c) Cowl Flap Setting 

(d) Landing Gear Position 

Issued: February 15.1975 

Revised: October 18, 1996 

5-1 

Q 1996 General Aviation Manufacturers Association 
(e) Environmental System Operation 

(f) Ice Protection System Operation 

(g) Runway Precipitation, Slope and Surface Type 

(h) Leariing Instructions 

5.17 Technique 

The technique or procedure necessary to duplicate 

the performance presented shall be included for those 

items of performance where the attainment of the 

predicted airplane performance requires a special 

sequence of actions. 

5.19 Examples 

Each graphical or tabular data presentation shall 

include one or more examples of the proper use of 

the data presentation unless its use is mciently 

simple that misuse or misunderstanding is 

improbable. 

The examples shall: 

(a) Illustrate the most general use of the 

presentation, avoiding special cases involving 

standard temperatures, reference weights, zero 

wind velocities, exact values of table entries or 

other occurrences not typical of actual situations. 

(b) Present assumed example data in the order in 

which it must be used in the graph or table. 

(c) Illustrate upon the face of the presentation graph 

or table, the successive entry of each assumed 

variable and the extraction of the end result. 

(d) Demonstrate any necessary subsidiary 

computations which must be performed upon the 

result extracted from the presentation. 

(e) Use assumed conditions, where applicable, the 

same as those used in the introduction to flight 

planning. 

5.21 Location of Examples, Associated Conditions and 

Technique 

Where possible, examples, associated conditions and 

technique should be presented on the same page as 

the chart. If space is not to include the 

necessary information, then the page facing the chart 

should be used. 

5.23 Weight 

Single engine airplanes require, as a minimum. data 

presented at the maximum weight. Data for multiengine airplanes should be presented for a range of 

specified weights. 

5.25 Airspeeds 

Airspeed values shall be expressed in knots. 

5.27 Distances 

All range distances shall be expressed in nautical 

miles. 

5.29 Pressure Altitude and Air Temperature 

Only pressure altitude shall be used in specifying 

airplane performance where altitude is involved. No 

reference shall be made to density altitude. All 

airplane performance making use of air temperature 

shall be presented in terms of degrees Celsius only, 

or in terms of both Celsius and, Fahrenheit 

simultaneously. If Celsius only is used, a conversion 

chart between Celsius and Fahrenheit will be 

provided. 

5.31 Wind Velocities 

The effective wind components along the runway 

shall be taken as 50% of headwind components and 

150% of tailwind components in all takeoff, landing, 

accelerate-stop, accelerate-go and other runway 

performance. 

5.33 Fuel Density 

For the purposes of range computations and related 

weight statements, the density of aviation gasoline 

shall be taken as 6.0 LB1U.S. Gal. and for aviation 

kerosene as 6.7 LB1U.S. Gal. 

5.35 Performance Formats and Rules 

The formats of performance presentations and related 

parameters and rules shall follow the examples in 

this Specification. If the format parameter or rule is 

inappropriate to the type of airplane, equivalents 

likely to achieve the same objective may be used. 

The notes on example graphs and tables in this 

Section are for guidance only. 

5.37 Minimum Performance Presentations for Single 

Engine Airplanes 

(a) Introduction to Performance and Flight 

Planning 

An actual trip, employing realistic or actual 

conditions, shall be planned utilizing as much of 

the performance section as possible. Include 

sample calculations and any information which 

will facilitate the proper use and application of 

performance information including an 

introduction to tabulated performance. (Figure 5- 

1) 

(b) Airspeed Calibration 

5-2 

Q 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
Data shall be presented as Calibrated Airspeed 

(CAS) versus Indicated Airspeed (IAS) assuming 

zero instrument error. The presentation for the 

normal airspeed system should include data for 

all flap configurations for which performance is 

quoted. The presentation for the alternate 

airspeed system, if applicable, should include 

data for cruise and landing flap configurations. 

All calibration data should cover the appropriate 

speed operating range. (Figure 5-2 or 5-3) 

(c) Altimeter Corrections 

Data shall be presented as altimeter correction 

versus indicated airspeed at the option of the 

manufacturer. The presentation should be 

included for those configurations and airspeed 

systems for which airspeed calibration data are 

presented. As a minimum. data should be 

presented at 5000 feet. A second table should be 

added if tabular data are presented at more than 

one altitude. (Figure 5-4 or 5-5) 

(d) Stall Speeds 

Data shall be presented as indicated airspeed and 

calibrated airspeed versus flap configurations 

(any flap position for which performance has 

been quoted) and angle of bank at maximum 

weight with throttle closed. Altitude loss of more 

than 100 feet and pitch below the horizon of 

more than thirty degrees during recovery from 

stalls should be added if applicable. (Figure 5-6 

or 5-7) 

(e) TakeoflDtstance 

Data shall be presented as distance versus 

outside air temperature, altitude and wind. Both 

ground roll and total distance over a 50 foot 

obstacle shall be included. The speeds required 

to attain these distances shall be scheduled in 

IAS Unless a higher margin is required by the 

certif~cation basis, for airplanes certificated after 

January 1, 1985, regardless of certification basis, 

the speed(s) at the 50 foot obstacle may not be 

less than 20% above the power-off stall speed 

for the same airplane configuration. The speed(s) 

for which ground roll distances were determined 

should be higher than the power-off stall speed 

for the same configuration. The chart should 

incorporate the limits of temperature and altitude 

where performance in the takeoff configuration 

has become marginal. The limiting criteria 

should involve the capability to climb in the 

takeoff configuration, free of ground effect, at 

50 fpm for retractable gear and 150 fpm for 

fixed gear airplanes. This limiting rate-of-climb 

value shall be identified clearly on the chart 

along with the power and conf@ation 

conditions. (Figure 5-9 or 5-10) 

(0 Rate-of-Climb 

Data shall be presented as rate-of-climb versus 

outside air temperature and altitude at maximum 

weight and maximum power approved for climb. 

Climb speed(s) should be either the best rate-ofclimb speed or an average best rate~f climb 

speed and scheduled in IAS. (Figure 5-13 or 5- 

14) 

(g) Time, Fuel and Distance to Climb 

Data shall be presented as time, fuel and 

distance to climb bm sea level versus altitude 

on a standard day (ISA). The climb speeds 

should be scheduled in IAS on the chart and 

preferably selected so that they will provide 

optimum range performance. The power 

setting@) used shall be no more than the 

maximum nonemergency climb rating. The 

associated conditions of power and fuel flow 

should be specified. (Figure 5-17 or 5-18) 

@) Cruise 

Data shall be presented as engine power settings, 

(manifold pressure, engine or propeller speed, 

fuel flow or whatever parameters are required to 

establish power) and true airspeed versus altitude 

and temperature. The format of the &se 

performance presentation is at the discretion of 

the airplane manufacturer, but should consider 

the following: 

1. The format should not rely on devices such 

as a power computer. 

2. The format should be simple to use for both 

preflight planning and inflight 

establishment of power. 

3. The proper use of the data should be 

explained. 

(i) Range Profdes 

Data should be presented as range of airplane 

versus altitude for various power settings and at 

least a full fuel loading. Range values should 

include an allowance for fuel to start, taxi, 

takeoff, climb and reserve. The following 

guidelines should be adhered to: 

1. For start, taxi and takeoff, allow 5 minutes 

of fuel flow at takeoff power. 

2. For climb, assume a sea level takeoff and 

use the data presented on the time, fuel and 

distance to climb chart. 

Issued: February 15,1975 

Revised: October 18, 1996 

5-3 

9 1996 General Aviation Manufacturers Assodatiin 
3. For all fuel loadings, the initial airplane 

weight should be the maximum allowable. 

4. Reserve shall be computed as 45 minutes at 

the cruise power to be used for the flight. 

The explanation information presented with 

the chart should explain how the reserve 

was computed. 

5. Range should be computed at standard day 

(ISA) temperatures. 

6. Range values should be included for at 

least the maximum and minimum power 

settings for which information has been 

presented in the Handbook. 

7. Range value shall not include parameters or 

variables that have not been presented in 

the Handbook. 

The sample graph is presented for only one fuel 

loading. Additional fuel loadings may be 

presented either as a secondary scale on the 

same chart or as an additional graph. (Figure 5- 

21) 

(j) Endurance Profile 

Data shall be presented as endurance time of 

airplane versus altitude for various power 

settings and at least a full fuel loading. 

Endurance should be calculated applying the 

same guidelines as for range prof~les and for the 

same conditions. (Figure 5-22) 

(k) Landing Distance 

Data shall be presented as landing distance 

versus outside air temperature altitude and wind. 

Both ground roll and the total distance over a 50 

foot obstacle shall be included. The speed@) at 

the 50 foot height point required to obtain the 

total distance shall be included. (Figure 5-27 or 

5-28) 

5.41 Minimum Performance Presentations for MultiEngine Airplanes 

(a) introduction to Performance and Flight 

Planning 

An actual trip, employing realistic or actual 

conditions, shall be planned utilizing as much of 

the performance section as possible. Include 

sample calculations and any information which 

will facilitate the proper use and application of 

performance information including introduction 

to tabulated performance. (Figure 5-1) 

(b) Airspeed Calibration 

Data shall be presented as Calibrated Airspeed 

(CAS) versus Indicated Airspeed (IAS) assuming 

zero inmment error. The presentation for the 

normal airspeed system should include data for 

all flap configurations for which performance is 

quoted. The presentation for the alternate 

airspeed system, if applicable, should include 

data for cruise and landing flap configurations. 

All calibration data should cover the appropriate 

speed operating range. (Figure 5-2 and 5-3) 

(c) Altimeter Corrections 

Data shall be presented as altimeter correction 

versus indicated airspeed and altitude at the 

option of the manufacturer. The presentation 

should be included for those configurations and 

airspeed systems for which airspeed calibration 

data are presented. If tabular data are presented 

repeat the table for additional altitudes. (Figure 

5-5 or 5-5) 

(d) Stall Speeds 

Data shall be presented as indicated and 

calibrated airspeed versus flap configurations 

(any flap position for which performance has 

been quoted), angle of bank and weight with 

throttles closed. If tabular presentation is used, 

repeat the table of additional weights. Altitude 

loss of more than 100 feet and pitch below the 

horizon of more than 30 degrees during recovery 

from stalls should be added if applicable. (Figure 

5-6 or 5-7) 

(e) Mmmum Takeof Weight ("Appiicable) 

Data shall be presented as maximum takeoff 

weight versus temperature and altitude. The 

chart shall be clearly identified as a limitation in 

accordance with Paragraph 5.7. (Figure 5-8) 

(f) AN Engines Operaring Take ofDistance 

Data shall be presented as distance versus 

outside air temperature, altitude, weight, and 

wind. Both ground roll and total distance over a 

50 foot obstacle shall be included. The speeds 

required to attain these distances shall be 

scheduled in IAS. The speed(s) at the 50 foot 

obstacle height may not be less than 20% above 

the power-off stall speed@) for the same airplane 

configuration or 10% above Vm, whichever is 

higher. The speed@) at the end of the ground roll 

distances@) may not be less than 5% above the 

power-off stall speed@) for the same airplane 

configuration or 5% above Vm, whichever is 

higher. The chart shall indicate the extremes of 

temperature and altitude where all engine 

performance in the takeoff configuration 

becomes marginal. These extremes should 

5-4 

O 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
involve the capability to climb in the takeoff 

configuration, fkee of ground effect, at 50 fpm 

for retractable gear airplanes and 150 fpm for 

fixed gear airplanes. This limiting rate-of-climb 

value shall be clearly identified on the chart, 

along with the power and configuration 

conditions. (Figure 5-9 or 5-10) 

(g) Accelerate-Stop Distance 

Data shall be presented as distance versus 

outside air temperature, altitude, weight and 

wind. Distances should include acceleration, 

deceleration and a time delay at engine failure 

speed equivalent to 3 seconds at the engine 

failure speed. Engine failure speed@) shall be 

the same as the lift-off speed($ assumed on the 

All Engines Operating Takeoff Distance chart 

except lower values may be used when a 

corresponding "accelerate-go" chart has been 

provided. (Figure 5-1 1 or 5-12) 

(h) Rate-of-Climb 

Data shall be presented as rate-of-climb versus 

outside air temperature, altitude and weight at 

the maximum power approved or as specified by 

the appropriate FAA requirements. Separate 

charts shall be included for the following: 

1. Rate-of-Climb-all engines operating with 

flaps set to the takeoff position and landing 

gear retracted. 

2 Rate-of-Climb-all engines operating with 

flaps set to the enroute position and landing 

gear retracted (If applicable) 

3 Rate-of-Climb-one engine inoperative with 

flaps set to the enroute position and landing 

gear retracted. 

4 Rate-of-Climb-Balked Landing. 

The climb speeds appropriate to each 

codiguration shall be scheduled in IAS. 

(Figure 5-13 or 5-14) 

Service Ceiling-One Engine hoperative 

Data shall be presented as service ceiling and 

outside air temperature versus weight. Service 

ceiling shall be the pressure altitude where an 

airplane has the capability of climbing 50 ftimin 

with one engine propeller feathered. (Figure 5- 

15 or 5-16) 

Erne. Fuel and Distance to Climb 

Data shall be presented as time, fuel and 

distance to climb hm sea level versus outside 

air temperature, altitude and weight. The climb 

speed(s) should be scheduled in IAS on the chart 

and preferably selected so that they will provide 

optimum range performance. The power 

s&g(s) should not exceed the maximum 

nonemergency climb power rating and all 

associated conditions should be specXkd. 

(Figure 5-1 7 or 5-18) 

(k) Cruise 

Data shall be presented as engine power setting 

(manifold pressure, engine or propeller speed, 

fuel flow or whatever parameters are required to 

establish power) and true airspeed verslls altitude 

and temperature. The effect of weight should 

also be scheduled if it sigaificantIy affect cruise 

performance. The format of the cruise 

performance presentation is at the discretion of 

the airplane manufacturer, but should consider 

the following: 

1. The format should not rely on devices such 

as a power computer. 

2. The format should be simple to use for both 

preflight planning and inflight 

establishment of power. 

3. The proper use of the data should be 

explained. 

(l) Range Profiles 

Data shall be presented as range of airplanes 

versus altitude for various power settings and at 

least a full fuel loading. Range values should 

include an allowance for fuel to start, taxi, 

takeoff, climb, descend and reserve. The 

following guidelines should be adhered to: 

For start, taxi, and takeoff, allow 5 minutes 

of fuel flow at takeoff power. 

For climb, assume a sea level takeoff and 

use the data presented on the time, fuel and 

distance to climb chart. 

For descent, assume a descent hm cruise 

altitude to sea level and use the data 

presented on the time, fuel and distance to 

descend chart. 

For all fuel loadings, the initial airplane 

weight should be the maximum allowable. 

Reserve shall be computed as 45 minutes at 

the cxuise power to be used for the flight. 

The explanation information presented with 

the chart should explain how the reserve 

was computed. 

Range should be computed at standard day 

(ISA) temperatures. 

Range values should be included for at 

least the maximum and minimum power 

Issued: February 15,1975 

Revised: October 18, 1996 

5-5 

Q 1996 General Aviation Manufacturers Association 
settings for which information has been 

presented in the Handbook. 

8. Range values shall not include parameters or 

variables that have not been presented in the 

Handbook. 

The sample graph is presented for only one fuel 

loading. 

Additional fuel loadings may be presented either 

as a secondary scale on the same chart or as an 

additional graph. (Figure 5-21) 

(m) Endurance Profile 

Data shall be presented as endurance time versus 

altitude for various power settings and at least a 

full fuel loading. Endurance should be calculated 

applying the same guidelines as for range 

profiles and for the same conditions. (Figure 5- 

22) 

(n) Holding Time 

Data shall be presented as holding time versus 

altitude and fuel required at a recommended 

power setting for holding. (Figure 5-23 or 5-24) 

(0) Time, Fuel & Distance to Descend 

Data shall be presented as time, fuel and 

distance to descend to sea level versus altitude. 

The conditions of speed and rate-ofdescent 

should be selected by the airplane manufacturer 

and specified. The format is the same as the 

graph or table for time, fuel and distance to 

climb for single engine aircraft. (Figure 5-25 or 

5-26) 

@) Landing Distance 

Data shall be presented as landing distance 

versus outside air temperature altitude, weight 

and wind Both ground roll and the total distance 

over a 50 foot obstacle shall be included. The 

speed@) at the 50 foot height point required to 

obtain the total distance shall be scheduled. 

Figure 5-27 or 5-28) 

5.42 Performance Presentations in Icing Conditions 

(a) Introduction 

Appendix C of FAR Part 25 defines specific 

parameters for certifkation of aircraft for 

operations in continuous maximum and 

intermittent maximum icing conditions. 

Atmospheric conditions, including large 

supercooled water droplets, freezing rain or a 

mixture of conditions, may exceed the FAR 

parameters and the capabilities of the certified 

ice protection system. This information shall be 

presented along with information to aid 

recognition of icing conditions which may 

exceed the certif~ed capabilities of the aircraft 

and its ice protection system. 

(b) Operations in Icing Conditions 

Data shall be presented by general statements of 

allowances necessary while operating in icing 

conditions or with residual ice on the airframe. 

(1) Data providing loss in rate of climb (FPM), 

reduction in cruise speed (K.IAS) and 

significant buffet and stall speed increase 

(KTS) for a selected ice accumulation and 

for residual ice remaining on the boots and 

unprotected areas of the airplane. 

(2) Data providing airspeed recommendations 

for operating with selected accumulations of 

ice or residual ice shall be presented. 

(3) Data providing airspeed recommendations 

and effects of boot operations prior to and 

during the landing approach. . 

(4) Recommendations for ATC holding 

operation in icing conditions for up to 45 

minutes (or less if so demonstrated). 

(5) Recommendations, if any, for engine 

operating parameter effects on the ice 

protection system or on performance of the 

engine in icing conditions. 

(c) Presentation Formats 

FAA Advisory Circular 23.14 19-2, Certif~cation 

of Part 23 Airplanes For Flight In Icing 

Conditions, contains recommendations for 

presentation of data and limitations. Reference 

to this Advisory Circular during preparation of 

the Pilot's Operating Handbook is encouraged. 

5-6 

0 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
LIST OF FIGURES 

Issued: February 15. 1975 

Revised: October 18. 1996 

Figure 

No . 

Introduction to Tabulated Performance .................................. 5-1 

Airspeed Calibration 

Graph .............................................................................. 5-2 

Table ............................................................................... 5-3 

Altimeter Correction 

Graph .............................................................................. 5A 

Table ............................................................................... 5-5 

Stall Speeds 

Graph .............................................................................. 5-6 

Table ............................................................................... 5-7 

Maximum Takeoff Weight ..................................................... 5-8 

Takeoff Distance 

Graph .............................................................................. 5-9 

Table ............................................................................... 5-10 

Accelerate-Stop Distance 

Graph .............................................................................. 5-11 

Table .............................................................................. 5-12 

Rate-of-Climb 

Graph .............................................................................. 5-13 

Table ............................................................................... 5-14 

Single Engine Service Ceiling 

Graph .............................................................................. 5-15 

Table ............................................................................... 5-16 

Time, Fuel & Distance to Climb 

Single Engine Airplane - Graph ....................................... 5-17 

Single Engine Airplane - Table ........................................ 5-18 

Multi-Engine Airplane - Graph ........................................ 5-19 

Multi-Engine Airplane - Table ......................................... 5-20 

Fuel and Time Required ......................................................... 5-20A 

Range Profile ........................................................................ 5-21 

Endurance Profde ............................................................... 5-22 

Holding Time 

Graph ............................................................................. 5-23 

Table ............................................................................... 5-24 

Time. Fuel & Distance to Descend 

Graph .............................................................................. 5-25 

Table ............................................................................... 5-26 

Landing Distance 

Graph .............................................................................. 5-27 

Table ............................................................................... 5-28 

Identification of Graphs or Tables - 

Single Engine Airplane .................................................... 5-29 

Multi-Engine Airplane ..................................................... 5-30 

5-7 

6 1996 General Aviation Manufacturers Association 
INTRODUCTION TO TABtUTED PERFORMANCE: 

Tabulations of performance are presented in increments of temperature, altitude and any other variables involved. Perfonmince for a given set of 

conditions may be approximated as foliows: 

Takeoff, climb, and landing - Enter tables at the next higher increment of altitude, temperature, weight and at zero wind. 

Cruise Enter tables at next lower increment of temperature, altitude and fuel loading; and the next higher increment of weight if applicable. 

To obtain exact performance values from tables, it is necessary to interpolate between the incremental values. 

The following is an excerpt from the Table for Takeoff Distances: 

EXAMPLE 

GIVEN: WEIGHT 

OLJTSIDE AIR 

TEMPERATURE 

NOTE DECREASE DISTANCE 4% FOR EACH 5 KNOTS HEADWIND 

30° 

PRESSURE 

ALTITUDE 

PRESS 

ALT 

FT 

2000 

4000 

2000 

4000 

WEIGHT 

LBS 

1 1,800 

11,000 

GROUND 

ROLL 

2720 

3230 

2415 

2860 

20" 

HEADWIND 

TOTAL TO 

CLEAR 50 

FT OBS 

4320 

5020 

3800 

4450 

GROUND 

ROLL 

2410 

2840 

2170 

2580 

FIND: TAKEOFF SPEEDS AT 

LIFT-OFF 

TOTAL TO 

CLEAR 50 

FT OBS 

3850 

4600 

3450 

4015 

TAKEOFF SPEED 

KNOTS - L4S 

50 FEET 

LIFT OFF 

101 

98 

GROUND ROLL 

50 FT 

118 

115 

TOTAL DISTANCE TO 

CLEAR 50 FT OBSTACLE 

APPROXIMATION METHOD: 

Read values at 11,800 lbs., 30°6 and 4.000 feet: 

11,275 LBS. Takeoff Speeds 

Lift-off 101 KIM 

50 feet 118 KIM 

25OC Ground Roll 3230 FEET 

Total to Clear 5020 FEET 

50' Obstacle 

3966 FT INTERPOLATION METHOD: 

The example weight is 34% of the difference between 

9.5 KNOTS 11,000 and 11,800 pounds. 

The example pressure altitude is 98% of the difference 

between 2000 and 4000 feet 

The example temperature is 50% of the difference 

between 20° and 30°6. 

Summary of Interpolated Values: 

Takeoff Speeds 

Li-off 99 KIM 

50 feet 116 KIAS 

Ground Roll 2818 FEET 

Total to Clear 4416 FEET 

50' Obstacle 

CorrPetion for Head Wind: 

For a 9.5 Knot Headwind, decrease distances by 7.6%. 

Ground RoU 2818-(7,676) (2818) = 2604 feet 

Total to Clear 44137.6%) (4416) = 4080 feet 

5-8 

Q 1996 General Aviatin Manufacturers Association 

Figure 5-1 

Iswed: February 15, 1975 

Revised: October 18,1996 
Figure 5-2 

issued: February 15, 1975 

Revised: October 1&19* 
AIRSPEED CALISRATION - NORMAL SYSTEM 

FLAPS FULL 

INDICATED AIR 

SPEED 110 KIAS 

CALIBRATED AIR 

SPEED 109 KCAS 

INDICATED AIRSPEED ASSUMES 

ZERO IHSTRUMENT ERROR. 

KlAS 1 70 1. 80 1 90 1100 1 120 1 140 1 160 I Fwtn IrcAs I79 1 85 .I 1 Irn IIIT Itss 1155 1 

KIAS - INDICATED AIRSPEED IN KNOTS 

KCAS CALIBRATED AIRSPEED IN KNOTS 

Figure 5-3 

5-1 0 

O 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
Figure 54 

Issued: February 15.1975 

Revised: Odober 18. 1996 5-1 1 

Q 1996 General Aviation Manufachrrers Assodabn 
ALTIMETER CORRECTION.- NORMAL SYSTEM 

FLAPS FULL 

INDICATED AIR 

SPEED 95 KlAS 

CORRECTION TO BE. 

ADDED -30 IT 

1. ADD CORREClWN TO INDICATED 

ALTIMETER READING. 

2 IAS AND INDICATED ALTITUDE ASSUME 

ZERO INSTRUMENT ERROR. 

COWDIT ION 

FLAPS UP 

Figure 5-5 

FLAPS 1/3 

FLAPS FULL 

5-1 2 

(B 1996 General Aviation Manufacturers Assodation 

CORRECTION TO BE ADDED FEET 

KNOTS IAS 

Issued: Fetxuary 15,1975 

Revised: Odober 1 8,1996 

80 

-10 

-10 

-16 

100 

-20 

-35 

-35 

120 

40 

-60 

60 

140 

60 

-80 

- 

160 

-90 

-1 10 

- 

1m 

-115 

-- 

- 
STALL SPEEDS 

COWtR loll 

NOTES: 1 MAXlMUM ALTITUDE LOSS OURING STALL RECOVERY IS APPROXIMATELY 800 

FEET 

2 MAXIMUM NOSE DOWN PITCH ATTITUDE AND ALTITUDE LOSS DURING RE 

COVERY FROM SINGLE ENGINE STALLS PER FAR 23.206 ARE APPROXIMATELY 

lo0 AND m FEET. RESPECTIVELY 

3. LANDING GEAR POSITION HAS NO EP FECT ON STALL SPEED. 

'I 

10 

WEIGHT - POUNDS 

WEIOHT 10.600 LBS 

FLAPS lOOl6 

ANGLE OF BANK 26' 

STALL SPEED 77 KNOTS IAS 

8Q KNOTS CAS 

20 30 40 30 

ANGLE OF BANK - DEGREES 
STALL SPEEDS 

POWER IDLE 

LANDING GEAR UP OR DOWN 

WEIGHT 4800 LBS 

LANDING GEAR DOWN 

FLAPS 100% 

ANGLE OF BANK t 6. 

STALL SPEED 58 KlAS 

64 KCAS 

1. MAXIMUM ALTITUDE LOSS DURlNG STALL 

RECOVERY IS APPROXIMATELY 800 FEET. 

2 MAXIMUM NOSE WWN PlTW AlTrrUOE AND 

ALTITUDE LOSS DURING RECOVERY FROM 

SINGLE ENGINE STALLS ARE 

APPROXIMATELY lo0 AND ZOal FEET, RESPECTIVELY 

3. LANDING GEAR POSITION HAS NO EFFECT ON STALL SPEEDS. 

Figure 5-7 

5-1 4 

Q 1996 General Aviation Manufacturers Assod?tion 

I 

WEIGHT 

LBS 

42iao 

Issued: Febnrary 15,1975 

Revised: Odober 18,1996 

CONDITION 

FLAPS UP 

FLAPS 11‘3 

FLAPSFULL 

2 

STALL SPEEDS % KNOTS 

ANGLE OF BANK - 

60" 

IAS 

85 98 

0" *5" 

81 

79 

30" 

IAS 

71 

68 

67 

IAS 

60 

57 

56 

93 

88 

IAS 

64 

61 

60 

CAS 

62 

78 

74 

CAS 

69 

68 

62 

CAS 

74 

71 

68 
MAXIMUM TAKEOFF WEIGHT 

OPERATING LIMITATION 

WAMPLE: 

PRESSURE MTlTUDE 

OAT 

I I I I I 1 

8000 gOQO 10.000 11.000 12XK)[) 13.000 14,000 

I 

MAXIMUM WEIGHT- POUNDS 

Figure 5-8 

Issued: Febntary 15,1975 

Revised: Odober 18,1996 

5-1 5 

Q 1996 General Aviation Manufeeturers lwocwm 
WWER 

FCACS 

LANDING (IEAR 

RUNWAY 

TAKEOFF POWER SET 

BEFORE BRAKE RELEASE 

0% 

RETRACT AFTER LIFT-OFF PAVED. LEVEL. DRY SURFACE 

TAKEOFF DISTANCE - 0% FLAPS 

OAT 26% PRESSURE ALTITUDE SO0 FEET 

TAKEOFF WElOHT 11276 LM HEADWIND COMrONEIlT 9.6 KNOTS (IROUND ROLL 2620 FEET TOTAL DISTANCE OVf R A 

W FOOT OBSTACLE 4200 FEET 

TAKEOFF SPEED AT LifT-WF 98 KIA5 

AT WFEET 116KNOTS IAB 
TAKEOFF DISTANCE 

ASSOCIATED CONDITIONS: EXAMPLE: 

WE R TAKEOFF POWER SET BEFORE BRAKE RELEASE 

FLAPS 0% 

LANDING GEAR RETRACTED AFTER LIFTOFF 

RUNWAY PAVED. LEVEL. DRY SURFACE 

WEIGHT 11 276 LBS 

OUTSIDE AIR TEMPERATURE 16'~ 

PRESSURE ALTITUDE 30MI FT 

HEADWIND COMPONENT 0.6 KTS 

GROUNDROLL 2804 FT 

TOTAL TO CLEAR W FT. 00s. 4080 FT 

TAKEOFF SPEED AT UR-OFF 99 KIAS 

60 FEET 1 16 UIAS 

NOTES: 

1. DECREASE DISTANCES 4% FOR EACH 5 KNOTS HEADWIND. FOR OPERAllON WITH TAILWINDS UP TO 10 KNOTS, INCREASE 

DISTANCES BY 8% FDR EACH 2.5 KNOTS. 

2. WHERE MSTANCE VALUE HAS BEEN DELETED, CLIMB PERFORMANCE AFTER Ll&-OFF IS LESS THAN - FTIMIN. 

RATE-OF-CLIMB 16 BASED ON ALL ENGINES OPERATINO At TAKWF POWER. OUR DOWN AT TAKEOFF SPEED. 

3. IF TAKEOFF POWER SET WITHOUT BRAKES APPLIED, THEN DISTANCE APPLY FR6M POiNT WHERE FULL POWER IS ATTAINED. 

TAKEOFF SPEED 1 

KHOTS % IAS ( ':? 1 (IROUN$c TOTAL ORWND F 1 a0c I 44% TOTAL 1 OROUND 1 TOTAL 1 OROUND I TOTAL 

60 FT OBS z 10 CLEAR BO FT OBS 

3460 4016 

4830 

7150 

ROLL 

2370 

2720 

3280 

3780 4676 

.... 

2100 

241 6 

2tMO 3400 

4070 

.... 

TO CLEAR 

60 FT OBI 

ROLL 10 CLEAR 

W FT 098 

3700 6300 

.... 
ACCELERATE - STOP DISTANCE - 0% FLAPS 

ASGQCIATED WNOITIONS: 

ME R 1. TAKEOFF POWER SET BEFORE BRAKE , - . . - . . 

RELEASE 

2. BOTH ENGINES IDLE AT ENGINE FAILURE 

SPEED AND REVERSE OPERATING 

ENGINE 

FLAPS On 

BRAKING MAXIMUM 

RUNWAY PAVED, LEVEL, DRY SURFACE 

ENGINE FAILURE WEED EXAMPLE: 

KNOTS \AS nar 

un w PRESWt3E ALTITUDE FEET WEIGHT 11,!276 LW 

HEADWIND COMPOMNT 0.6 KNOTS 

a I 

.. 

0000 m I ACCELERATE . STOP DISTAHCE Boo0 rn ENGINE FAILURE SPEED WOO f BET W KNOTS IAS 
ACCELERATE - STOP + OK FLAPS 

*#06QATED CLM101TtOMS: WLE: 

POWER 1. TAKMFF WWER SET BEFORE BRAKE WEIGHT 112% LBS 

RELEASE OUTSIDE AtR TEWRATURE 280C 

2 BOTH ENGINES IDLE AT ENGINE PRmURE ALTITUDE S988 FT 

FAILURE SPEED AND REVERSE HEADWIND COMPONENT 9.5 KTS 

ommffi ENGINE. 

FLAPS w 

BRAKlNG WlMW 

RUNWAY PAVED. LEVEL DRY SURFACE 

APPROXIMATION METHOD 

ACCELERATEDISTANCE 5870 FT 

ENGINE FAILURE SPEED 98 KlAS 

INTERPOUTIOFI METHOD 

ACCELERATESTOP 

DISTANCE 5077 FT 

ENGINE FAILURE SPEED 98 KlAS 

NOTE: 

1. DECREASE DISTANCES 4% FOR EACH 6 KNOTS HEADWIND. FOR OPERATIONS WITH 

TAlLWINDS UP TO 10 KNOTS, INCREASE DISTANCES BY 696 FOR EACH 2.5 KNOTS 

2. DISTANCES INCLUDE A FAILURE RECOGNITION TIME OF 3 SHX)NDS. 

Issued: February 15,1975 

Revised: October 18,1996 

WEIGHT 

LBS11500 

11000 

10000 

Figure 5-12 

5-1 9 

@ 1996 General Aviation Manufacturers Associatkn 

ENGINE 

FAILURE 

SPEED 

QD 

96 

91 

PRESSURE 

ALTITUDE 

FEET 

SL 

2000 

4000 

6rm 

8000 

10000 

SL 

MOO 

4000 

6rm 

8000 

10000 

SL 

MOO 

4fm 

6000 

8000 

10000 

O'C I 10°c I 2O0c I MOc I .Oat 

ACCELERATE STOP DISTANCE 1. FEET 

4025 

4370 

4725 

63m 

8MO 

68al 

3800 

4080 

44W 

5000 

SZ5 

g375 

3310 

3560 

3825 

4325 

4900 

5475 

4110 

4570 

5080 

5740 

~6490 

7400 

3960 

4310 

4750 

5350 

g05Q 

8880 

3460 

3750 

4130 

4625 

523s 

5900 

4370 

4810 

5450 

6180 

6975 

8010 

4160 

4570 

5120 

5725 

6520 

7480 

3620 

3950 

4420 

4960 

5610 

8420 

4650 

5150 

5870 

6670 

7600 

8770 

4390 

4890 

5525 

6150 

7100 

- . 3840 

4190 

4750 

5315 

8075 

- 

5100 

5710 

6500 

7300 

- 

- 

4770 

5390 

6060 

8800 

.- 

- 

4180 

4860 

5280 

5840 

.- 

- 
RATE-OF-CLIMB - ONE ENGINE INOPERATIVE 

ASSOCIATED CONDltlW POWER MAXIMUM CONTINUOUS 

FLAPS Ou 

LANDlNG GEAR UP BLtEDAlR VALVES CLOSED 

INOPERATIVE PROPELLER FEATHERED Boo0 

OAT 

P~ESS. ALTITUDE VO~FEEI 

MlDHT 11.W LM 

RATEaCLIM# 

CLIME WEED 

OUTSIDE AIR TEMPERATURE OC WEIGHT - WNDS 
RATE4F-CLIMB - ONE ENGINE INOPERATIVE 

ASSOCLATED CONDITIONS: EXANIPLE: 

POWER 

LANDING GEAR 

FLAPS 

PRESSURt ZATION 

LNOPERATIVE PROPELLER 

FUEL MtXrURE 

MAX. CONT. AT 2800 RPM WEIGHT 4400 LBS 

UP PRESSURE 

UP ALTITUDE 3000 ff 

OFF OUTSIDE AIR 

FEATHERED TEMPERATURE 10'~ 

AT RECOMMENDED LEANING 

SCHEDULE. CLIMB SPEED 89 KlAS 

RATEQF-CLlMB 273 FT/MIN 

WEIGHT 

LBS. 

6s00 

4500 

Issued: February 15,1975 

Revised: October 18, 1996 

Figure 5-14 

5 - 21 

Q 1996 General Aviation Manufacturers Associatiin 
SERVICE CEILING - ONE ENGINE lNOPERATIVE 

WWFR . - - - - . . ~XIUUW CONTINUOUS OAT AT MEA roOc 

LANDING GEAR UP 

BLEED AIR VALVE CLOSED 

IMPERATIVE PROPELLER FEATHERED 

ROUTE SEGMENT WEA t1,lrao FEET 

maw 1~us 

FLAPS UP 

NOTE: SERVICECEILING IS THE PRESSURE ALTITUDE WHERE AIRPLANE HAS CAP&BILITY OF CLIMBING 

W FTfWllNUTE WITH WE PROPELLER FEATHERED. 

-m -60 -50 40 -30 -20 -10 o 10 20 30 40 50 BO 70 

OUTSWE AIR TEMPERATURE - OC 

Figure 5-15 

5 - 22 

O 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18, 1996 
SERVICE CEf LING - ONE ENGINE INOPERATlVE 

ASSOCIATED CONDITIONS: EXAMPLE: 

POWER MAX. CONTINUOUS OAT AT MEA -S"C 

FLAPS UP ROUTE SEGMENT 

LANDING GEAR UP MEA am FT 

BLEED AIR VALVE CLOSED WEIGHT 4305 LBS 

INOPERATIVE PROPELLER FEATHERED 

SERVICE CEILING IS ALTITUDE WHERE AIRCRAFT HAS CAPABILITY 

OF CLlMBING 50 FT/MIN WITH ONE ENGINE FEATHERED. 

PRESSURE 

ALTITUDE 

FEET 

4000 

5000 

7000 

8000 

9000 

loo00 

11000 

!lmo 

13000 

14000 

OUTSIDE AIR TEMPERATL 

-20 I -10 1 -0 I 10 

Figure 5-16 

Issued: February 15,1975 

Revised: October 18,1996 

5 - 23 

63 1996 General Aviation Manufacturers Association 
TIME, FUEL, AND DISTANCE TO CLIMB 

ASSOCIATED U3NDlTlOM 

POWER 2825 RPM, FUU THROmE 

MlXNRE FULL RICH 

TEMPERATURE STANOARO DAY IlSAI 

FUEL OENSJlY 8.0 LBSJGAL 

EXAMPLE: 

WEIGHT 

POUNCX; I 

3300 

2800 

AIRPORT ALTITUDE 

CRUfSE ALTITUDE 

CLIMB SPEED 

KNOTS IAS 

I 

130 

130 

FEET 

8800 FEET 

TIME TO CLIMB (17 -3.6) 186 MINUTES 

FUEL TO CUMB t 180 - 4% 137 LBS 

DISTANCE TO CtiMB (4S.6 -8.51 37.0 N M 

4000 

3m 

zoo0 

loo0 

S.L. 

I I I I I I I 

o w tia iiaiolzoo 250 

i FUEL TO CLIMB - POUNDS 

DISTANCE TO CLIMB- NAUTICAL MILES 

Figure 5-17 

5 - 24 

8 1996 General Aviation Manufacturers Association 

Issued: February 15, 1975 

Revised: October 18,1996 
TIME, FUEL, AND DISTANCE TO CLIMB 

ASSOCIATED CONDITIONS: EXAMPLE: 

POWER MAX. M.P. AT 2700 RPM ALTITUDE 17,500 FT 

FUEL MIXTURE RECOMMENDED LEANING WEIGHT 3,350 LBS 

SCHEDULE 

FUEL DENSITY 6.0 LBS/GAL INDICATED AIR 

FLAPS 0% SPEED 89 KIAS 

TEMPERATURE STANDARD DAY (ISA) RATE-OF -CLIMB 765 FT/MIN 

{SEE NOTE 2, FOR TIME 23 MIN 

APPROX. PERFORMANCE FUEL 61 LBS 

ABOVE ISA) DISTANCE 40 N.M. 

NOTES: 

1. DISTANCES SHOWN ARE BASED ON ZERO WIND. 

2. FOR TEMPERATURES ABOVE STANDARD, DECREASE RATE-OF-CLIMB 40 FT/M1N 

FOR EACH 5QC ABOVE STANDARD DAY TEMPERATURE FOR PARTICULAR ALTITUDE. 

PRESSURE 

ALTITUDE 

FT 

SEA LEVEL 

CLIMB 

SPEED 

WAS 

90 

90 

90 

90 

88 

84 

WEIGHT 

LBS 

3600 

31 00 

2600 

3MM 

3100 

2600 

3600 

3100 

2600 

3600 

3100 

2600 

3600 

31 00 

2600 

3600 

3100 

2600 

RATE OF 

CLIMB 

FT/MI N 

1030 

1300 

1660 

950 

1220 

1570 

860 

1120 

1470 

740 

loo0 

1320 

540 

780 

f.080 

190 

330 

630 

Figure 5-18 

TlME 

MIN 

0 

0 

0 

5 

4 

3 

11 

8 

6 

18 

14 

to 

37 

20 

14 

13 

29 

20 

iL 

DISTANCE 

N.M. 

0 

0 

0 

9 

7 

8 

20 

16 

12 

35 

28 

20 

55 

40 

30 

95 

65 

- 45 

Issued: Febnrary 15, 1975 

Revised: October 18,l 

5-25 

(9 1996 General Aviation Manufacturers Association 
Figure 5-19 

5 - 26 

(G4 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
TIME, FUEL, AND DISTANCE TO CLIMB 

POWER MAX. M.P. AT 2276 RPM OAT AT TAKEOFF ISA + GOC 

FUEL MIXTURE RECOMMENDED LEAN OAT AT CRUISE IS - PC 

LANDING GEAR UP AIRPORT PRESSURE ALTITUDE 4MK1CT 

FLAPS a CRUISE ALTITUDE 15000 FT 

INITIAL CLIMB WEIGHT 11600 LB6 

TIME TO CLIMB 1123) 9 MIN 

FUEL f 0 CLIMB (141-37) 104 LBS 

DISFANCE TO CLIMB (34-8) 26 N.M. 

- NOTE: 

1. DISTANCES SHOWN ARE BASED ON ZERO WIND. 

2 ADD 66 LBS. OF FUEL FOR START, TAXI AND TAKEOFF. 

Issued: FebFuary 15,1975 

Revised: October 18, 1996 

TEMPERATURE 

ISA + 10'~ ISA 1 1SA - 10-c 

TAKEOFF 

WEIGHT 

LBS 

PRESSURE 

ALTITUDE 

FT 

SEA LEVEL 

Figure 5-20 

CLIMB 

SPEED 

KIAS 

150 

150 

150 

130 

130 

120 

120 

5-27 

9 1996 General Aviation Manufacturers Association 
INTENTIONALLY LEFT BLANK 

5 - 28 

6 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
FUEL AND TIME REQUIRED 

CONDITIONS: 

5150 Pounds 

Recommended Lean Mixture for Cruise 

Standard Tempemure 

NOTE: 

Fuel required includes the fuel used for engine start, taxi, takeoff, normal climb, descent 

and 45 minutes reserve. Time required includes the time during a normal climb and 

descent. 

DISTANCE - NAUTICAL MILES 

Figure 5-20A 

Issued: February 15, 1975 

Revised: October 18, 1996 

5 - 28A 

9 1996 General Aviation Manuhcturers Association 
5 - 28B 

O 1996 General Aviation Manufacturers Association 

Figure 5-21 

Issued: February 15,1975 

Revised: October 18,1996 
ENDURANCE PROFILE 

STANDARD DAY 

ASSOCIATED CONDITIONS: 

WEIGHT 8706 LBS BEFORE ENGINE START 

FUEL AVIATION KEROSENE 

FUEL DENSITY 8.7 LBSlGAL 

INITIAL FUEL LOADING 384 U. S. GAL (2673 LBSI 

PROpELl.FR SPEED 1900 RPM 

NOTE: ENDURANCE INCLUDES START, TAXI, CLlMB AND 

DESCENT WITH 46 MINUTES RESERVE FUEL AT MAXIMUM 

RANGE POWER. 
5 - 30 

Q 1996 General Aviation Manufadurers Association 

Figure 5-23 

Issued: February 15,1975 

Revised: Odober 18,1996 
HOLDING TlME 

ASSOCIATED CONDITIONS: EXAWLES: 

TORQUE SETTING 650 FT LBS 1. FUEL AVAILABLE FOR 

PROPELLER SPEED 1900 RPM HOLDING 440 LBS 

PRESSURE ALTITUDE FT 

REQUIREMENT/ 

OR AVAILABLE 

% POUNDS 

100 

200 

300 

400 

500 

600 

700 

800 

900 

1 OW 

1100 

1200 

1300 

1400 

1500 

1600 

PF 

S.L. 

HOLDING TIME 1.04 HRS 

(1 HR, 2 MIN) 

2. REQCftRED HOLDtNG 

TIME 45 MIN 

(-75 HRS) 

HOLDING PRESSURE 

ALTITUDE 8000 FT 

FUEL REQUIRED 319 LBS 

Issued: February 15, 1975 

Revised: October 18, 1996 

Figure 5-24 

5 - 31 

(a 1996 General Aviation Manufacturers Association 
TIME, 

MSOCIATED CONDITIONS: 

FUEL, 

POWER AS RECURED TO DESCEND 

AT 1000 FT/MIN 

AND DISTANCE TO 

ALTfNDE DESCENT SPEED 

KNOTS IAS 

sim~ozepoo 

20.m TO S.L. 

LANOING GEAR UP 

FLAPS 0% 

PROPELLER SPEED 1900 RPM 

INITIAL ALTITUDE 

FINAL ALT%TUDE 

i7m FEET 

5850 FEET 

TIME TO DESCEND (17 - 5.8) 11 MINUTES 

FUEL TO DESCEND (142 -62) BO US 

DESCEM DISTANCE IS - 8) 45 NM 

0 50 100 1 So 

DESCENT DISTANCE - NAUTICAL MILES 

Figure 5-25 

5 - 32 

8 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18, $996 
TIME, FUEL, AND DISTANCE TO DESCEND 

ASSOCIATED CONDITIONS: EXAMPLE: 

POWER AS REQ'D. FOR 1000 FPM INITIAL ALTITUDE 17,000 FT 

FLAPS UP FINAL ALTITUDE 5650 FT 

UND1NG GEAR UP 

At RSPEED 200 MAS TIME TO DESCEND (17-6) 11 MlM 

FUEL TO DESCEND (143-62) 81 LBS 

DISTANCE TO DESCEND (6920) 48 N.M. 

Issued: February 15, 1975 

Revised: October 18, 1996 

Figure 5-26 

b 

5 - 33 

Q 1996 General Aviation Manufacturers Association 

PRESSURE 

ALTITUDE 

FEET 

FUEL 

tBS 

223 

197 

163 

130 

95 

57 

0 

TIME 

MIN 

DfSTANCE 

N.M. 

118 

97 

88 

57 

36 

18 

0 

3fJ,m I 30 

25.000 25 

-- 20,000 

15,000 

10,000 

5,000 

SEA LEVEL 

20 

15 

10 

5 

0 
-. 

Figure 5-27 

5 - 34 

Q 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
LANDING DISTANCE 

ATED CONDITMNS: 

POWER RETARDED TO MAINTAIN 

500 FTIMIN ON FINAL APPROACH 

FLAPS 100% 

RUNWAY PAVED, LEVEL, DRY SURFACE 

BRAKING MAXIMUM 

- NOTE: 

WEIGHT 10301 LBS 

OUTSIDE AIR TEMPERATURE ~SOC 

PRESSURE ALTITUDE 6650 FT 

HEADWIND COMPONENT 9.5 KTS 

GROUND ROLL 1333 FT 

TOTAL OVER 60 FT OBSTACLE 2249 FT 

APPROACHSPEED 96 KlAS 

1. OECflEASE DISTANCES 4% FOR EACH 5 KNOTS HEADWIND. 

FOR OPERATIONS WITH TAILWINDS UP TO 10 KNOTS, INCREASE DISTANCES BY 6% FOR EACH 2.6 KNOTS. 

SPEED O"C WOc M'C 30' c 40°c 

LBS A LT 

( KIAS 1 FEET I I 110 FT OBS I 1 SO FT 06s I I SOFT OBS 

I I I I I I I I I I I I 
ORDER 

1 

2 

3 

* 4 

5 

6 

* 7 

8 

9 

10 

*I1 

*12 

13 

14 

15 

16 

SINGLE ENGINE AIRPLANES 

IDENTIEICATION OF GRAPHS OR TABLES 

IN TYPICAL ORDER OF PRESENTATION 

INCLUDING OPTIONAL ITEMS 

T1"IZE 

Intruduction to Performance and Flight Planning 

Airspeed Calibration 

Altimeter Conection 

Fahrenheit to Celsius Temperatu~ Conversion 

Stall Speeds 

Takeoff Distance 

Minimum Takeoff Distance 

Rate-of-Ciimb 

Tie, Fuel and Distance to Climb 

Cruise 

Cruise speeds 

Fuel Ffow vs Brake Horsepower 

Fuel and Time Required 

Range Profile 

Endurance Profile 

Landing Distance 

* Optional items may'be required by regulation for some airplane models. 

Figure 5-29 

5 - 36 

@ 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
Issued: February 15, 1975 

Revised: October 18, 1996 

MULTI- ENGINE AIRPLANES 

IDENTIFICATION OF GRAPHS OR TABLES 

IN TYPICAL ORDER OF PRESENTATION 

INCLUDING OPTIONAL ITEMS 

ORDER 

1 

2 

3 

4 

5 

* 6 

* 7 

* 8 

9 

15 

* 16 

17 

* 18 

19 

*20 

*2 1 

22 

23 

24 

25 

26 

*27 

28 

29 

*30 

3 1 

*32 

33 

*34 

3 5 

TITLE 

Introduction to Performance and Flight Planning 

Airspeed Calibration-Nod System 

Airspeed Calibration-Alternate System (If Applicable) 

Altimeter Correction-Nod System 

Altimeter Correction-Alternate System (If Applicable) 

Indicated Outside Air Temperature Correction 

Fahrenheit to Celsius Temperature Conversion 

Terrain Clearance Limitations 

Stall Speeds 

Takeoff Distance 

Minimum Takeoff Distance 

Accelerate-Stop Distance 

Accelerate-Go Distance 

Rate-of-Climb-All Engines Operating 

(naps set to take-off position) 

Climb Gradient-One Engine Inoperative 

(Flaps set to take-off position) 

Rate-of-Climb-All Engines Operating 

(naps set to emute position) 

Time, Fuel and Distance to Climb 

Rate-of-Climb-One Engine Inoperative 

(Flaps set to enroute position) 

Service Ceilings-One Engine Inoperative 

Rate-of-Climb-Balked Landing 

Cruise-All Engines Operating 

Cruise Speeds-Maximum Recommended 

Cruise Power-All Engines Operating 

Fuel and Tie Required 

Range Prof~le 

Range Payload Trade-Off-All Engines Operating 

Endurance Profile 

Cruise Performance-One Engine 

Inoperative 

Holding Time 

Pressurization Controller Setting 

for Landing 

Landing Distance 

*Optional items may be required by regulation for some airplane models. 

Figure 5-30 

5 - 37 

9 1996 General Aviation Manufacturers Association 

SECTION 6 

WEIGHT AND BALANCE AND EQUIPMENT LIST (as applicable) 

TABLE OF CONTENTS 

Paragraph 

6.1 General 

6.3 Airplane Weighing Procedure 

6.5 Weight and Balance Record 

6.7 Weight and Balance Determination for Flight 

6.9 Equipment List 

Page 

SECTION 6 

WEIGHT AND BALANCE AND EQUIPMENT LIST (as applicable) 

6.1 General 

This Section of the Pilot's Operating Handbook shall 

contain all weight and balance information required 

by the Federal Aviation Regulations and this 

Specification. Additional weight and balance and 

related information may be provided. The figures in 

this Section of the Specification are for illustrative 

purposes only. The manufacturer should use formats 

appropriate to the specific airplane and Handbook 

size. 

6.3 Airplane Weighing Procedure 

This paragraph describes the procedure for 

establishing weight and moment (relative to 

reference datum) of the empty airplane. Each 

Handbook shall have an "Airplane Weighing Form" 

that includes an airplane side view showing the 

location of weighing points (using jacking points or 

undercarriage) relative to the datum line. The form 

shall include tables for recording and correcting 

weighing data, and for establishing "basic empty 

weight" and moment. (See Figure 6-1) The 

calculation procedures and "basic empty weight" 

data used in loading calculations shall be explained. 

6.5 Weight and Balance Record 

Each Handbook shall contain a weight and balance 

record The record shall start with the "as delivered 

ueight and balance data. Explain how to maintain 

this record when changes to the weight or moments 

of the airplane are made so that accurate starting data 

is available to calculate the weight and c. g. during 

normal operation of the airplane. (See Figure 6-2) 

Provide weight and moment values for nod items 

of a load. (See Figure 6-6) 

Instead of (or in addition to) the weight and balance 

loading form, the manufacturer may provide a device 

to be used to calculate weight and balance. 

Instructions for its use shall be provided. 

6.9 Equipment List 

The manufacturer shall provide an equipment list in 

this Section, in a separate document appended to the 

Handbook, or as a separate document. If the 

equipment list is not contained in this Section, state 

its location. In addition, this Section may contain a 

comprehensive list of equipment available for 

installation by the manufacturer. 

The equipment list shall contain all required or 

optional equipment installed in the particular 

airplane when delivered. The list may be a suitable 

notation in a comprehensive list of available 

equipment. Equipment without significant effect on 

the weight or balance of the airplane need not be 

listed. 

Describe each equipment list item and show its 

weight and airplane location, with respect to the 

datum. The weight and arm for optional equipment 

may be shown as the net difference between standard 

and optional equipment, if noted accordingly. All 

parts of an integral installation map be combined into 

a single equipment list item if variation of weight or 

arm is not significant. (see Figure 6-7.) 

6.7 Weight and Balance Determination for Flight Equipment list items may be identified by an item 

number and may be grouped logically, using This paragraph describes the procedures to calculate headings such as "Propeller and Propeller weight and moment for various phases of a planned Accessories", 'Engine and Engine Accessories", flight and to ensure that the center of gravity is "Landing Gear", "Electrical Equipment", "Interior within approved limits. Equipment", "Autopilot", etc. If the equipment list is 

A Weight and Moment Limit diagram shall be used 

to describe the c. g. limits. (See Figure 6-3) 

a comprehensive list of equipment available for 

installation by the manufacturer, a check ($ or "T 

may be used to indicate the items installed when the 

Handbook for the specific airplane was prepared and A weight and balance loading form and an placed in the aixplane. A manufacturer may use an explanation of the calculation procedure shall be "X" to indicate standard or required equipment and a provided (See Figures 6-4 and 6-5 for examples). check ($ to indicate installed optional equipment. 

Issued: February 15,1975 

Revised: October 18, 1986 

6-1 

Q 1984 General Aviation Manufacturers Association 
Alternates for equipment may be listed under the 

same item number. (See Figure 6-7, Item 62) For 

installations made up of a number of units which 

my 

be located at various places in the airplane, each unit 

should be listed separately. (See Figure 6-7, Item 

402) 

6-2 

O 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
AIRPLANE WEIGHING FORM 

MODEL XXX 

SERIAL REGISTRAT ION 

NUMBER NUMBER DATE 

REFERENCE 

DATUM 

LEVELING PROVISIONS 

Long~tudinal - Right side of Fuselage 

WING JACK POINT Stations 238 

STA. 186.2 Lateral - Bottom of Fuselage 

Station 154 

STA. 99.5 STA. - Station, a position along the fuselage measured in inches from the reference datum 

AIRPLANE AS WEIGHED. 

(rncluding full oil and operating fluids but no de fuel*) 

Left Wing 

Right Wing 

I POSITION I SCALE READING 

. ---- I 

AIRPLANE TOTAL AS WEIGHED (W) 1 1 1 

SCALE 

ERROR 

'Note: Normally weighed at factory without usable fuel. 

Figure 6-1 

* 

NET 

WEIGHT 

C G arm of a~rplane as we~ghed. 

(126.0)Wn 171.9 - W = inches aft of reference datum 

186.7)Wn 

or 1862 - = inches aft of reference datum 

W 

BASIC EMPTY WEIGHT ANDC G 

Issued: February 1 5, 1975 

Revised: October 18,1986 

ITEM 

Subtract - Usable Fuel (if 

applicable) 

Add - Drainable Unusable 

Fuel (if weighed with 

6-3 

Q 1984 General Aviation Manufacturers Association 

fuel drained) 

(6 Ibs per gallon) 

Optional Equipment (if applicable) 

BASIC EMPTY WEIGHT 

MOMENT 

(LBS - IN.) 

WEIGHT 

(LBS) 

1 

C G ARM 

ON-) 
WEIGHT AND BALANCE RECORD 

(Continuous History of Changes in Structure or Equipment Affecting Weight and Balance) 

I AIRPLANE MODEL ( SERIAL NUMBER I PAGENUMBER 
Issued: February 15, 1975 

Revised: October 18, 1986 

WEIGHT AND MOMENT LIMITS 

CENTER OF GRAVlTY +INCHES AFT OF REFERENCE DATUM 

EXAMPLE 

AT 10.250 LBS AND 18.300 MOMENT1100 

CG LOCATION IS 188.5 IN. AFT OF REFERENCE DATUM 

Figure 6-3 

6 - 5 

0 1984 General Aviation Manufacturers Associatiin 
WEIGHT AND BALANCE LOADING FORM 

Totals must be within approved weight and C G limits. It is the responsibility of the airplane owner and the 

pilot to insure that the airplane is loaded property. The Basic Empty Weight C G is noted on the Airplane 

Weighing Fwm. If the airplane has been. altered, refer to the Weight and Balance Record for this 

information. 

Figure 6-4 

4 

6-6 

Q 1996 General Aviation Manufacturers Association 

MOMENT (IN. LBI. 

Basic Empty Weight 

Front Seats 

Middle Seats 

Rear Seats 

Fwd Luggage 

Rear Luggage 

1 

Issued: February 15,1975 

Revised: October 18,1996 

WEIGHT 

Main Wing Tank Fuel (Usable) 

Aux Wing Tank Fuel (Usable) 

Other 

Totals 
WEIGHT AND BALANCE LOADING FORM 

SERIAL NO. REGISTRATION NO. DATE 

ITEM 

3CCUPANTS OR CARGO 

:ABINET CONTENTS 

'OTAL PAY LOAD 

ARM WEIGHT 

'Totals must be within approved weight and 

C G limits. It is the responsibility of 

the airplane owner and the pilot to insure 

that the airplane is loaded properly. The 

Basic Empty Weight C G is noted on the 

Airplane Weighing Form, If the airplane 

has been altered, refer to the Weight and 

Balance Record for this information. 

Issued: February 15, 1975 

Revised: Odober 18,1986 

Figure 6-5 

ITEM WEIGHT MOM/100 

BASIC EMPW 

WEIGHT 

PAY LOAD 

WEIGHT (LESS FUEL) 

(sub-total) 

(Do not exceed 

max. zero fuel 

weight) 

MAIN WlNG TANK 

FUEL LOADING 

AUX. WlNG TANK 

FUEL LOADING 

RAMP CONDITION 

{Sub-totail 

LESS FUEL FOR 

START & TAXI 

TAKEOFF 

CONDITION 

LESS FUEL TO 

DESTl NATION 

LANDING WEIGHT 

i 

6 - 7 

(B 1984 General Aviation Manufacturers Association 
FUEL 

BAGGAGE 

WEIGHT 

--pic 

WEIGHT WING TANKS 

6 - 8 

9 1996 General Aviation Manufacturers Association 

FORWARD REAR 

FS 170 TO 190 

ARM 180 

Figure 6-6 

4UX WING 

TANKS 

ARM 93 EiL$ 

56 

84 

112 

140 

1 67 

190 

195 

223 

251 

WMENT1100 

I 2g I 11 I 15 

mto. 9F WAR 

ICENTER SUITS 

REMOVED1 

ARM 1W 

Issued: February 15,1975 

Revised: October 18,1996 

AFT OF SPAR 

(CENTER 81 AFT 

SEATS REMOVED) 

ARM 146 
Format of Equipment List: 

EQUIPMENT LIST 

Manufacturer Model 

SEXIAL NO. REGISTRATION NO. DATE: 

JTEM 

NO. 

a. Airspeed Indicator 

No. 41507-6 

b. Airspeed Indicator 

NO. 41507-5 

Autopilot, 

Gyro 

Amplifier 

Servo 

Figure 6-7 

MARK IF 

INSTALLED 

WEIGHT 

(POUNDS) 

.7 

.6 

15 

2 

5 

ARM 

(INCHES) 

% 

96 

90 

90 

80 

Issued: February 15,1975 

Revised: October 18,1986 

6-9 

Q 1984 General Aviation Manufacturers Association 

SECTION 7 

DESCRIPTION OF ME AIRPLANE AND ITS SYSTEMS 

TABLE OF CONTENTS 

Paragraph Page 

General ............................................................................ 7-1 

We ........................................................................ 7-1 

Flight Controls ............................................................. 7-1 

Instrument Panel .............................................................. 7-1 

Flight btruments ............................................................. 7-1 

Ground Control ................................................................. 7-1 

Wing Flaps, Dive Brake or Spoiler Systems ...................... 7-2 

Landing Gear .................................................................... 7-2 

Baggage Compartments .................................................... 7-2 

Seats, Seat Belts, and Shoulder Harnesses ......................... 7-2 

Doors, Windows and Exits ................................................ 7-2 

Control Locks ................................................................... 7-2 

Engine ............................................................................... 7-2 

Propeller ........................................................................... 7-3 

Fuel System ..................................................................... 7-3 

Hydraulic System ........................................................... 7-3 

Brake System .................................................................... 7-3 

Power Steering ................................................................ 7-3 

Electrical System .............................................................. 7-3 

Lighting Systems .............................................................. 7-3 

Auxiliary Power Unit ........................................................ 7-3 

Heating, Ventilating. Defrosting & Air Conditioning ........ 7-3 

Cabin Pressurization System ............................................. 7-4 

Oxygen System ................................................................. 7-4 

Pitot Pressure Systems ....................................................... 7-4 

Static Pressure Systems ..................................................... 7-4 

Vacuum or Pneumatic System ........................................... 7-4 

Automatic Devices in the Control System ......................... 7-4 

Stall Waming or Angle of Attack System .......................... 7-4 

Icing Equipment ............................................................. 7-4 

Avionics ............................................................................ 7-4 

Comfort Features .............................................................. 7-4 

Cabin Features .................................................................. 7-4 

Windshield Wipers ............................................................ 7-4 

SECTION 7 

DESCRIPTION OF THE AIRPLANE AND ITS SYSTEMS 

General 

This Section of the Pilot's Operating Handbook shall 

describe the airplane in a manner considered by the 

manufacturer to be most informative to the kind of 

pilot considered most likely to operate the airplane. 

The paragraph order and detail in this Section need 

not be followed in a Handbook. The purpose of this 

Section is to provide a comprehensive guide and 

check list of items to be considered in the Handbook 

prepared by the manufacturer. This format may, of 

course, be used in its entirety or in part. 

Generally, in describing the airplane or its system, 

third person wording should be used. (For example: 

The nose wheel is provided with a shimmy damper to 

keep the wheel from shimmying while rolling on the 

ground.) Nomenclature and terminology should be 

consistent. Terms which are not well known should 

be defined. Standard abbreviations listed in Section 1 

are acceptable. 

Reference to other books or to other sections of the 

manual should be kept to a minimum. 

Where applicable the following topics should be 

included. 

Airframe 

Flight controls 

Ground control 

Wing flaps. dive brakes and spoiler systems 

Landing gear 

Baggage compartments 

lZlrplane tiedown provisions and jack points 

Seats. seat belts, and shoulder harnesses 

Doors, windows, and exits 

Control locks 

Engine 

Propeller 

Fuel system 

Hydraulic system 

Brake system 

Power steering system 

Electrical system 

Lighting 

Auxiliaq power unit 

Heating, ventilating, defrosting and air conditioning 

systems 

Cabin pressurization system 

oxygen system. 

Instrument panel 

Pitot pressure system 

Static pressure system 

Vacuum or pneumatic system 

Flight instruments 

Autopilot, flight director, and automatic devices in 

the control system 

Stall warning or angle-of-attack system 

Icing equipment 

Avionics 

Comfort features 

Cabin features 

Windshield wipers 

7.3 Airframe 

(a) Describe structure of fuselage, wings, and 

empennage. 

(b) Describe seating arrangements available. 

7.5 Flight Controls 

(a) Describe control surfaces. 

(b) Describe operating mechanism-sketches may 

be provided. 

(c) Explain trimming arrangements. 

(d) Explain any interconnect arrangement. 

(e) If controls are boosted explain the systems. 

7.7 Instrument Panel 

(a) Provide a drawing or picture of the instrument 

panel. 

(b) Name and explain the use of the instruments, 

lights, switches and controls found on the panel. 

(c) If an annunciator panel is installed, explain how 

it operates. 

7.9 Flight Instruments 

(a) Briefly describe and explain principle of 

operation of any new kinds of flight instruments. 

(b) Explain how to check them for proper operation 

and how to recognize a malfunction. 

7.11 Ground Control 

(a) Describe how the pilot mechanically controls 

nose wheel or tail wheel. 

Issued: February 15, 1975 

Revised: October 18, 1996 

7-1 

O 1996 General Aviation Manufacturers Association 
(b) Describe minimum radius of turn for taxiing and 

ground handling. 

7.13 Wing Flaps, Dive Brake or Spoiler Systems 

(a) Describe aerodynamic surfaces. 

(b) Explain how they are operated. 

(c) Describe how application of these affects pitch 

attitude, airspeed trim, and staU speed. 

(d) Explain what provisions are made to prevent 

asymmetric conditions. 

7.15 Landing Gear 

(a) Describe construction. 

(b) Describe retraction mechanism if provided. 

(c) Describe shock absorption system. 

(d) Describe wheel brakes. 

(e) Explain emergency extension system. 

(f) Explain how warning system functions. 

7.17 Baggage Compartments 

(a) Explain locations. 

(b) Explain restrictions. 

(c) Describe tie down provisions and explain how to 

tie down baggage. 

(d) Explain door warning system. 

(e) Give tips on loading. 

(f) Warn against putting or allowing children in a 

baggage compartment. 

(g) Warn against carrying hazardous material 

anjwhere in the airplane. 

7.19 Seats, Seat Belts, and Shoulder Harnesses 

(a) Describe how to adjust the seats. 

(b) Explain how to use the seat belts and shoulder 

harnesses. 

(c) Include warnings and restrictions. 

7.21 Doors, Windows and Exits 

(a) Describe how to operate and lock doors, 

windows and exits. 

(b) Explain any procedures or warnings necessary 

for the doors, exits, windows or windshield 

wipers. 

(c) Discuss how to close a door or window if it 

opens accidentally in flight and any restrictions 

there may be on purposely opening in flight. 

(d) Give precise instructions for using emergency 

exits. 

7.23 Control Locks 

(a) Explain how to engage control locks or secure 

control surfaces. 

(b) Warn against forgetting to remove control locks. 

7.25 Engine 

(a) Descn'be the engine, giving the following as 

deemed necessary: 

1. Manufacturer and model number 

2. Type of engine-number of cylinders, type 

of compressor, etc. 

3. Ratedpower 

4. Rated engine speed 

5. Gear reduction if applicable 

6. Accessories normally installed 

7. Supercharging/rurt>ocharging or other 1 

augmentation 

8. Explain restrictions, warnings, tips 

(b) Describe the engine controls including: 

1. Throttle or power control 

2. Propellercontrol 

3. Mixturecontrol 

4. Cooling controls 

5. Turbocharger controls 

6. Friction lock 

(c) Describe the engine instrumentation 

1. Describe briefly the method of operation 

2. Give limits of readings and typical values 

where applicable 

(d) Proper operation and care of the engine when 

new and after the break in period should be 

described. 

(e) Describe the lubrication system including: 

1. Typeof system 

2. I.nsmmentation 

(f) Describe ignition system 

(g) Describe the air induction system including: 

1. Path of flow of the air 

2. Icing protection 

3. Filtering 

4. Supercharginflurbocharging 

5. Explain restrictions, warnings, tips 

I 

(h) Describe the exhaust system including 

carburetor heat, muff heater, and flow to 

turbocharger (if appropriate). 

(i) Describe the carburetor or fuel injection system 

including provisions for priming. 

(j) Describe the cooling system including cowl 

flaps. 

(k) Describe the engine starting system. 

(l) Describe simply the accessories including: 

1. Oil pump 

2. Fuel pumps 

7 - 2 

8 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
3. Hydraulic pump 

4. Airpump 

5. Tachometer 

6. Torque meter 

7. Electrical power source 

8. Propellersyncbronizer 

9. Exhaust gas temperature probe 

(m) Describe any unique engine mounts including 

shock mounts. 

(n) If an engine fire detection or extinguishing 

system is available, describe, give principle of 

operation, and explain how to use these. 

(0) Describe any gear reduction system in the 

engine. 

@) Abnormal operations should be discussed 

briefly. This should be held to the minimum that 

will help a pilot to correct a situation or enable 

him to describe it to a mechanic. It should not be 

a maintenance procedure. 

7.27 Propeller 

(a) Describe the propeller and its opeamtion if pitch 

can be varied. 

(b) Explain how the propeller should operate. 

(c) If appropriate, discuss feathering, Weathering, 

and reversing. 

(d) Explain cautions, warnings, restrictions, and 

idiosyncrasies. 

(e) A cutaway drawing of variable pitch propellers 

may be included. 

7.29 Fuel System 

(a) Describe the system, provide a good schematic. 

and explain the operation. 

(b) Discuss unusable fuel. 

(c) Explain fuel management. 

(d) Explain how to avoid and notice fuel 

contamination. 

(e) Explain and discuss how the heater gets fuel (if 

appropriate). 

(f) Explain crossfeed and fuel transfer (if 

appropriate). 

(g) Discuss the fuel venting system and consequence 

of allowing it to become plugged. 

01) Explain the fuel measurement system and 

discuss need for monitoring and calibrating. 

(i) Explain restrictions, warnings and operating tips. 

7.31 Hydraulic System 

(a) Explain what items use hydraulic pressure. 

(b) Describe the primary and auxiliary systems. 

(c) Provide one or more schematic diagrams of the 

system. 

(d) Describe controls and btxumentation of the 

system. 

(e) Discuss no& operation. 

(f) Dixuss abnormal operation. 

(g) Explain restrictions, warnings and operating tips. 

7.33 Brake System 

(a) Descriie the brake system. 

(b) Discuss how to get maximum braking and 

maximum life out of the brakes. 

(c) Explain how to recognize impending problems 

and what to do if malfunctions occur. 

NOTE: At the manufachuds option, brake 

system description and discussion may be 

covered under paragraph 7.15, Landing Gear. 

7.35 Power Steering 

If nose wheel power steering is installed: 

(a) Desmie the system. 

(b) Explain how to use it. 

(c) Discussrestrictions. 

7.37 Electrical System 

(a) Making use of simpwed schematics and 

drawings explain how this system operates, 

including warning devices and control feannes 

in use. 

(b) Discuss capacity and load shedding. 

(c) Explain circuit protection. 

(d) Discuss use of ground power units and battery 

charging. 

(e) Explain restrictions, warnings and operating tips. 

7.39 Lighting Systems 

(a) Describe the various interior and exterior 

lighting systems. 

(b) Explain how to troubleshoot malfunctions. 

(c) Discuss how to check and operate the systems. 

7.41 Auxiliary Power Unit 

(a) If the airplane has a built-in auxiiiary power 

unit, describe it and explain how it fits in with 

the electrical system. 

(b) Explain operation of the unit. 

(c) Explain restrictions and warnings. 

7.43 Heating, Ventilating, Defrosting And AirConditioning Systems 

Issued. February 15, 1975 

Revoed: October 18,1996 

7-3 

Q 1996 General Aviation Manufachrrerr AsmckWn 
(a) Using dnwhgs as aids, describe each of the 

systems. 

(b) Explain how to get maximurn benefit and 

control using the controls provided. 

7.45 Cabin Pressudtion System 

If the airplane is pded: 

(a) Describe the system. 

(b) Fixplain how to operate it. 

(c) Explain how this system ties in with the heating, 

ventilating, defrosting and air-conditioning 

systems. 

(d) Explain how to recognize potential problems and 

handle emergencies. 

7.47 Oxygen System 

(a) Describe the oxygen system if one is ofiered. 

(b) Discuss restrictions or warnings. 

7.49 Pitot Pressure Systems 

(a) Describe the pitot pressure systems. 

(b) Explain anti-icing provisions, if installed 

7.51 Static Pressure Systems 

(a) Describe the static pressure systems. 

(b) Explain the alternate static systems if available. 

(c) Discuss effects of heating and ventilating 

systems and of open windows on the alternate 

static system. 

NOTE: At the manufacturer's option, static 

pressure systems description and discussion may 

be combined with Paragraph 7.49, Pitot Pressure 

Systems. 

7.53 Vacuum Or Pneumatic System 

(a) Using schematic diagrams describe the system 

and the items which use it 

(b) Explain how de-icing boots tie in with the 

system, if installed. 

(c) Explain how the system can be checked. 

(d) Discuss how a failing system can be recognized. 

(e) Discuss restrictions and warnings. 

7.55 Automatic Devices In The Control System 

(To be included at manufacturer's option) 

(a) Describe in simple terms the devica which are 

offered. 

(b) Explain how to check and operate the devices. 

(c) Discuss how to recognize a malfunction and how 

to handle the situation. 

7.57 Stall Wdg Or Angle of Attack System 

(a) If either of these devices is installed explain 

whether it is required equipment. 

(b) Explain the principle of operation. 

(c) Explain how to chedc the system and use it 

(d) Discuss how to recognize a malfimction and 

when not to depend on it 

7.59 Icing Equipment 

(a) Descriie anti-icing or de-icing equipment 

available, and list that required for flight through 

known icing conditions. 

(b) Descriie how each item 

1. Operates, 

2. Can be check84 

3. Can be recognized as malfunctioning, 

4. Might be corrected if malfunctioning. 

(c) Explain resaictions imposed on each item. 

7.61 Avionics (To be included at manufacturer's 

option) 

(a) De~~lie items which are standard and explain 

their function and how they are operated. 

(b) Refer to Section 9, supplements for description 

andlor operating instructions for avionic 

equipment which is installed. 

7.63 Comfort Features 

(a) Items such as toilets, relief tubes, sinks, etc. may 

be descn'bed and explained. 

7.65 Cabin Features 

(a) Special features such as storm window, fire 

extinguisher, food bar. tape players, special 

doors, etc. may be described and their use 

explained if standard. 

7.67 Windshield Wipers 

(a) Explain how to operate windshield wipers if 

installed. 

(b) Explain any restrictions. 

(c) Describe how to correct a malfunction. 

7-4 

Q 1996 General Avtabon Manufacturers Aswuabo . . 

n 

Issued: February t5,1B75 

Rwd: October 16,1996 
SECTION 8 

HANDLING. SERVICING AND MAINTENANCE 

TABLE OF CONTENTS 

Paragraph Page 

Introduction ...................................................................... 8-1 

Airplane Inspection Periods ............................................... 8-1 

Preventive Maintenance that may be Accomplished 

by a Certificated Pilot ...................................................... 8-1 

Alterations or Repairs to Airplane ..................................... 8-1 

Gmund Handling ............................................................... 8.1 

Servicing ........................................................................... 8-1 

Cleaning and Care ............................................................. 8-1 

Prolonged Out-of-Service Care ......................................... 8-2 

SECTION 8 

HANDLING, SERVICING AND MAINTENANCE 

8.1 General 

This Section of the Pilot's Operating Handbook shall 

describe ways an operator of an airplane can ensure 

that the necessary handling, servicing and 

maintenance of the airplane can be accomplished. 

The user of this Handbook is the pilot - a person of 

undefined background - not a mechanic or 

technician. 

An appropriate warning or note shall be contained in 

this Section to inform the operator that he is 

responsible for ensuring that all airworthiness 

directives are complied with and that the handling, 

senicing and maintenance of the airplane is done 

when required and in accordance with the Federal 

Aviation Regulations. In order to meet this 

responsibility, this Section should contain - 

(a) A recommendation that airplane operator 

establish contact with the dealer or certified 

service station for service and information; 

(b) A recommendation that all correspondence 

regarding the airplane include the airplane serial 

number (state where the serial number can be 

found); and 

(c) A notation that service manuals and part 

catalogs are available and an explanation as to 

how these may be procured and kept up to date. 

8.3 Airplane Inspection Periods 

This paragraph shall contain information on the 

airplane (and components thereof) inspection 

periods. It should cover FAA required inspections 

(such as the annual and, in some cases, the 100 hour 

inspections) and manufacturer recommended 

inspections (such as the daily, 25-hour, 50-hour, 

etc.). Special inspection intervals for airplane 

systems an& possibly, for liie limited parts, may be 

covered in this paragraph or there may be a reference 

to another section or another document where such 

inspection intervals may be found. This paragraph 

should also explain that, in addition to the 

established inspections, other inspections may be 

required by Airworthiness Directive. There should be 

a reference to the Federal Aviation Regulation 

(FAR'S 43 and 9 1 or other applicable regulations) as 

to who may perform the required and manufacturer 

recommended inspections. 

8.5 Preventive Maintenance That May Be 

Accomplished By A Certificated Pilot 

(a) A certificated pilot who owns or operates an 

airplane not used as an air carrier is authoxized 

by FAR Part 43 to perform limited preventive 

maintenance on his airplane. The Handbook 

should refer to FAR Part 43 for list of things the 

pilot may do. 

Pilots operating aircraft of other than U.S. 

registry should refer to the regulations of the 

countq of certification for information on 

preventive maintenance that may be performed 

by pilots. 

(b) Include note to state that all other maintenance 

required on airplane is to be accomplished by 

appropriately licensed personnel and that 

airplane dealer or service station should be 

contacted for further information. 

(c) Include note to state that preventive maintenance 

should be accomplished in accordance with the 

appmpriate airplane service or maintenance 

manual. The Handbook should advise pilots to 

obtain a service manual prior to performing 

preventive maintenance to be sure that proper 

procedures are followed. 

8.7 Alterations or Repairs to Airplane 

(a) Note that alterations or repairs to airplane must 

be accomplished by licensed personnel. 

(b) Point out that the FAA should be contacted prior 

to aq alterations on airplane to insure that 

airworthiness of the airplane is not violated. 

8.9 Ground Handling 

Discuss the following items: 

1. Towing procedure 

2. Parking 

3. Tie down or mooring 

4. Jacking and leveling 

8.11 Servicing 

Include information for servicing the aircraft with 

proper fuel and oil. Note any necessary precautions 

that should be observed. 

Issued: February 15,1975 

Revised: October 18,1996 

8-1 

Q 1996 General Aviation Manufacturers Association 
8.13 Cleaning and Care 

(a) Cleaning procedures for the following aircraft 

elements should be provided: 

1. Exterior Cleaning such as: 

Painted surfaces 

Propeller 

Engine 

2. Interior Cleaning such as: 

Wood surfaces 

Metal surfaces 

Cloth surfaces 

Leather surfaces 

Plastic lrim 

Carpets 

Toilets 

8-2 

Q 1996 General Aviation Manufacturers Association 

(b) Items to be included in the cleaning procedure 

should be: 

Recommended cleaning agents. 

Caution notes regarding use of unauthorized 

cleaning agents and possible hazards of using 

authorized ones. 

8.15 Prolonged Out-of-Service Care 

Include information for preparing the airplane for 

prolonged out-of-service care and for returning the 

airplane to service. 

Issued: February 15,1975 

Revised: October 18 1996 
SECTION 9 

TABLE OF CONTENTS SUPPLEMENTS 

9.1 General ............................................................................. 9-1 

9.3 Supplement Scope ............................................................. 9-1 

9.5 Supplement Issuance ........................................................ 9-1 

9.7 Supplement Identification : .............................................. 9-1 

9.9 Page Numbering ............................................................... 9-1 

9.11 Structure of Supplements .................................................. 9-1 

SECTION 9 

SUPPLEMENTS 

9.1 General 

(a) This Section of the Pilot's Operating Handbook 

shall contain the appropriate Supplements 

(operating information) necessary to safely and 

efficiently operate the airplane when equipped 

with the various optional system and equipment 

not provided with the standard airplane. 

(b) Supplements may be prepared by the Handbook 

producer, supplied to the Handbook producer by 

the equipment supplier and inserted, as supplied, 

into the Handbook, or supplied to the airplane 

owner when he purchases new equipment after 

the airplane (and Handbook) has been delivered. 

The content of this Section of the Specification 

should be interpreted so as to foster the goal of 

providing the necessary information to the pilot. 

(c) The Table of Contents required by paragraph 0.9 

of this Specification may be in the form of a log 

(or list) of the Supplements. A log of additions 

of or revisions to Supplements, if needed ,may 

be incorporated into this Section instead of the 

Log required by paragraph 0.43 of this 

specification. 

9.3 Supplement Scope 

Each Supplement shall normally cover only a single 

system, device, or piece of equipment such as an 

autopilot, electric trim, or an area navigation system. 

Systems consisting of several components, such as 

ice protection systems, may have Supplements for 

each component, such as propeller boots, wing and 

empennage boots, or heated airspeed static source, if 

the equipment is FAA Approved by component and 

@) Supplements may be issued only to owners of 

airplanes equipped with the subject systems or 

equipment. This results in tailored Pilot's 

Operating Handbook and considerable record 

keeping; 

9.7 Supplement Identification 

Unless the Supplements are integrated within this 

Section of the Handbook (and thus derive their 

approval from approval of the Handbook), each 

Supplement shall have a cover or title page with the 

unique supplement identification, date of issue (or 

revision, it appropriate) and signature and title of the 

certificating or approving authority. 

9.9 Page Numbering 

Supplement page numbers shall consist of a 

statement of the consecutive page numbers, such as 

"1 of 5", "2 of 5", etc. 

9.11 Structure of SuppIements 

Each Supplement shall be a self-contained. miniature 

Pilot's Operating Handbook with the following as a 

minimum: 

(a) Section 1, General. The purpose of the 

Supplement and the systems or equipment to 

which it specifically applies shall be stated. FAA 

Approved Supplements shall be identified as 

such, and it shall be made clear that when the 

subject system or equipment is installed, the 

associated Supplement must be in the Pilot's 

Operating Handbook at all times. 

marketed individually. The effect of anti-icing or de- (b) Section 2, Limitations. Any changes to the 

icing systems on the approval of the airplane for limitations, instrument markings, or placards of operating in known icing conditions should be the basic Limitations (Section 2) of the Pilot's clearly defined in the limitations section of the Operating Handbook shall be stated. If there is no supplements. change, a statement to that effect shall be made. 

9.5 Supplement Issuance 

All Supplements for any particular airplane shall be 

issued by one or the other of the methods below: 

(a) All Supplements may be issued to all owners of 

the airplane model covered by the Handbook. 

This method is recommended as minimizing 

errors of distribution, and also informs owners of 

the availability of systems and equipment. 

(c) Section 3, Emergency Procedures. Emergency 

Procedures associated with the subject 

installation shall be presented in a checklist form 

when order of action is essential to safety, and 

any changes to the basic Emergency Procedures 

(Section 3) of the Pilot's Operating Handbook 

shall be stated. If there is no change, a statement 

to that effect shall be made. 

Issued: February 15,1975 

Revised: October 18 1996 

9-1 

Q 1996 General Aviation Manufacturers Association 
(d) Section 4, Normal Procedures. Normal (e) Section 5, Performance. The effect, if any, of the 

Procedures associated with the subject subject installation upon airplane Performance as 

installation shall be presented in a check list shown in the basic Performance (Section 5) of the 

form when order of action is essential to safety, Pilot's Operating Handbook shall be indicated. If 

and any changes to the basic Normal Procedures there is no change, a statement to that effect shall be 

(Section 4) of the Pilot's Operating Handbook made. 

shall be stated. If there is no change, a statement 

to that effect shall be made. 

9-2 

0 1996 General Aviation Manufacturers Association 

Issued: February 15,1975 

Revised: October 18,1996 
SECTION 10 

SAFETY AND OPERATIONAL TIPS (OPTIONAL) 

TABLE OF CONTENTS 

Paragraph Page 

10.1 General ........................................................................... 10-1 

10A. 1 Alphabetical Index (Optional) ...................................... 10A- 1 

SECTION 10 

SAFETY AND OPERATIONAL TIPS (OPTIONAL) 

10.1 General 

A Safety and Operational Tips section may be 

incorporated in the Handbook. It may contain: 

Safety information of a general nature. such as-- 

(1) kinds of information and rules to be found in 

FAA publications; 

(2) how to conduct various airplane inspections; 

(3) medical problems and information (vertigo, 

hypoxia, fatigue, affects of scuba diving, etc.); 

and 

(4) any other information that would enhance the 

safe use of the airplane. 

(5) Child restraint systems: 

A small child should use an approved child 

restraint seat. The child should not be held or 

share a seat belt with another person. 

Acceptable child restraint seats are defined in 

publications such as Advisory Circular 9 1-62. 

Operational tips of a general nature, such as - 

(1) general weather information and sources and 

how to use the information; 

(2) general fuel conservation information (such as 

why it pays to keep the exterior of the airplane 

clean); 

(3) tips on operating in mountainous areas (or in 

desert areas or on grass or gravel mways, etc.); 

and 

(4) any other information that would enhance the 

operational use of the airplane. 

Issued: February 15,1975 

Revised: October 18, 1996 

10-1 

8 1996 General Aviation Manufacturers Association 

ALPHABETICAL ORDER 

At the option of the manufacturer, a con~prehensive alphabetical index may be included following the last section in the 

handbook. 



SPECIFICATION FOR CONTINUING 

AIRWORTHINESS PROGRAM 

(A Supplement to the Airplane's Maintenance Manual) 

GAMA SPECIFICATION NO. 7 

issued: March, 1991 

1st edition 

prepared and published by 

GENERAL AVIATION MANUFACTURERS ASSOCIATION 

Suite 801 

1400 K Street, NW 

Washington, DC 20005 

(202) 393- 1 500 

The primary document containing the procedures for the continued airworthiness of an 

airplane is the airplane's maintenance manual. A document prepared in accord with this 

Specification supplements, and is designed for use with, that manual. 

Copyright 1990 by 

General Aviation Manufacturers Association 

Washington, D.C. 

All rights reserved. No part of this document may be reproduced in any form without 

permission in writing from the publisher. 

CAP 

LIST OF EFFECTIVE PAGES 

CHAPTER 

SECTION 

SUBJECT 

COVER 

TITLE PAGE 

LIST OF EFFECTIVE PAGES 

RECORD OF REVISIONS 

PREFACE 

CONTENTS 

SECTION I - PHYSICAL REQUIREMENTS 

SECTION II - CONTINUING AIRWORTHINESS 

PROGRAM DOCUMENT 

PRESENTATION 

SECTION Ill - SAMPLE CAP 

Issued: March, 1991 

PAGE 

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ii 

iii 

N 

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1-1 

1 -2 

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DATE 

March, 1991 

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I ' 1991 General Aviation Manufacturers Association 
THIS PAGE INTENTIONALLY BLANK 
CAP 

PREFACE 

This Specification was developed by the General Aviation Manufacturers Association as 

guidance for airplane, engine and component manufacturers in preparing Continuing 

Airworthiness Program lnspection Documents (which may also be called Continuing 

Airworthiness Programs or CAPs). CAPs may be prepared for all types of general 

aviation airplanes and components certificated under the applicable Federal Aviation 

Regulations. 

A CAP supplements the airplane's maintenance manual (or Instructions for Continuing 

Airworthiness) which is the primary document containing the procedures for the 

continuing airworthiness of the airplane. Some airplanes, particularly relatively simple 

airplanes, may not need CAPs because adequate information to maintain their continuing 

airworthiness throughout their useful lives is contained in the airplane's maintenance 

manual. In such cases, a CAP need not be published. If a manufacturer elects to 

provide comprehensive inspection information to supplement the basic airplane 

maintenance manual, this Specification is an example of, and establishes a standard for, 

a Continuing Airworthiness Program lnspection Document. Instead of, or in addition to, 

this example of style and format for a CAP, a manufacturer may use its publication style 

manual or another appropriate style manual. 

The Specification was developed with the objective of minimizing the cost to, and efforts 

of, general aviation airplane owners and operators and maintenance personnel by 

standardizing the format and general content of Continuing Airworthiness Programs. 

Standardization will enhance safety through uniform interpretation of inspection 

requirements contained in Continuing Airworthiness Programs prepared in accord with 

this Specification. For the purposes of this Specification, "airplane" refers to the airframe 

and all related components specified in the Type Certificate or made available as options 

by the airplane manufacturer. 

This Specification has been developed in response to Federal Aviation Administration 

(FAA) Advisory Circular AC 91-60, The Continued Airworthiness of Older Airplanes, and 

Advisory Circular AC 91-56, Supplemental Structural lnspection Program for Large 

Transport Category Airplanes. These FAA advisory circulars provide specific information 

regarding continued airworthiness requirements for the manufacturer and owner/operator. 

Advisory Circular 91 -56 provides "Guidelines for Development of Continuing Airworthiness 

Programs" to which this Specification closely adheres. 

In addition to understanding FAA Advisory Circulars AC 91-60 and AC 91-56, familiarity 

with GAMA Specification No. 2, Manufacturers Maintenance Data and Air Transport 

Association of America Specification No. 100, Specification for Manufacturers Technical 

Data, will aid in the preparation of a CAP for a specific airplane. 

It is intended that manufacturers retain and exercise reasonable judgement and latitude 

in the content of their publications with respect to depth and scope of coverage. In order 

to achieve the objectives of this Specification (enhance safety, reduce efforts, minimize 

Issued: March, I991 

iii ' 1991 General Aviation Manufacturers Association 
CAP 

costs), each manufacturer is expected to reasonably adhere to the Specification content 

and arrangement in order to provide consistent, industry standardized Continuing 

Airworthiness Programs. If a company publication style manual is used (so as to maintain 

continuity of the company "style" for all of its publications), the format and layout should 

follow this Specification to the extent practicable. 

This Specification contains references to the Federal Aviation Administration (FAA) and 

the Federal Aviation Regulations (FARs). If the Specification is used to prepare a 

Continuing Airworthiness Program for acceptance by an airworthiness authority other than 

FAA, the appropriate authority and its regulations may be substituted. 

Questions on interpretation and proposed changes to this Specification should be 

submitted to General Aviation Manufacturers Association, Suite 801, 1400 K Street, N.W., 

Washington, D.C. 20005. 

iv 

" 1991 General Aviation Manufacturers Association Issued: March. 1991 
CAP 

CONTENTS 

TITLE PAGE 

LIST OF EFFECTIVE PAGES ...................................... i 

RECORD OF REVISIONS .......................................... ii 

PREFACE .................................................... iii 

SECTION I . PHYSICAL REQUIREMENTS ............................ 1-1 

BinderTypeandPageSue ............................................... 1-1 

Paper. PrintingandTypeSize ............................................. 1-1 

Pageidentification ..................................................... 1-1 

Copystandards ....................................................... 1-3 

Figurel-1 -PageLayout .................................................. 1-2 

TabDividers .......................................................... 1-3 

Identifying Revised Material ............................................... 1-3 

SECTION It . CONTINUING AIRWORTHINESS 

PROGRAM DOCUMENT ............................... 2-1 

Contents ............................................................ 2-1 

Explanation of Contents ................................................. 2-1 

SECTION Ill . SAMPLE CAP ...................................... 3-1 

Figure 3-1 . CAP Cover .................................................. 3-2 

Figure3-2-CAPTalePage ............................................... 3-3 

Figure 3-3 . Intentionally Blank Page ......................................... 3-4 

Figure 3-4 . List of Effective Pages ......................................... 3-5 

Figure 3-5 . Record of Revisions ........................................... 3-6 

Figure 3-6 . Table of Contents ............................................. 3-7 

Figure 3-7 . Applicability Statement ......................................... 3-8 

Figure 3-8 . Objectives Statement .......................................... 3-9 

Figure 3-9 . Objectives Statement (Continued) ................................ 3-10 

Figure 3-10 . Objectives Statement (Continued) ............................... 3-11 

Figure 3-1 1 . Intentionally Blank Page ....................................... 3-12 

Figure 3-12 . Technical Document Reference .................................. 3-13 

Figure 3-13 . Intentionally Blank Page ....................................... 3-14 

Figure 3-14 . Listing of Continuing Airworthiness Program Inspections (List Form) ...... 3-15 

Figure 3-15 . Listing of Continuing Airworthiness Program Inspections (Block Form) .... 3-16 

Figure 3-16 . Continuing Airworthiness Program Inspection ....................... 3-17 

Figure 3-17 . Continuing Airworthiness Program Inspection ....................... 3-18 

Issued: March. 1991 

v ' 1991 General Aviation Manufacturers Association 
THIS PAGE JNTENTlONALLY BLANK 
CAP 

SECTION I - PHYSICAL REQUIREMENTS 

1. Bbrfer Type and Page Size 

Documents must be readily revisable. They may be in loose-leaf form with a durable, multi-ring 

cover, permanently bound, 'Fiche', or another appropriate form. if in loose-leaf form, use 

'standard", or commonly used page sizes. 

2. Paper, Printing and Type Size 

Use white paper with good strength characteristics and of sufficient weight and substance to 

eliminate excessive show-through when printed on both sides. In meeting these requirements, 

consideration may be given to limiting paper bulk. Use a form of printing that results in a black 

image suitable for reproduction. Copy density must be uniform throughout the page. 

Print interim changes (interim to a republication of the document), except fiche or microfilm copy, 

on colored stock. Weight and substance may be governed by the printing process used. 

Prepare basic text in 10- or 12-point type. Use 14-point uppercase bold for the word WARNING 

and 10-point uppercase bold for the WARNING TEXT. Use 12-point uppercase bold for the word 

CAmON and 10-point uppercase for the CAUTION TEXT. Use 10-point uppercase bold for the 

word NOTE and 10-point mixed case for the Note Text. First, second and third level heads and 

captions should be distinctive in size or styie or both. Type styie is determined by the Document 

producer based on the equipment available and good judgement. See Figure 1-1. 

3. Page Identification 

Number the pages of CAPs containing only one section in sequence with section identification. 

Number the pages of multi-section CAPs with section number and a dash (i.e., "1 -" for all pages in 

the "Physical Requirements" section) followed by the serial number of the page beginning with "1' 

for each section (e.g., Page 1-1, 1-2, etc.) 

Number the pages in each appendix with the Appendix letter (or number) and a dash (i.e., "G-" for 

all pages in the appendix) followed by the serial number of the page beginning with "1" for each 

appendix (e.g., Page G-1, G-2, etc.) 

Print the page number and date of issue or revision at the bottom of each page. Locate the page 

number in the lower right corner and the date of issue in the lower left corner, for odd pages. 

Locate the page number in the lower left corner and the date of issue in the lower right corner, for 

even pages. See Figure 1-1. 

Pages of permanently bound or "Fiche" Documents need not be dated. Table of Contents pages 

must be dated but need not be numbered. 

Issued: February, 1991 

1-1 " 1991 General Aviation Manufacturers Association 
CAP 

TEXT LIMITNO BORDER 

NOTES 

1 MANUFACTURER'S MASTHEAD IDENTIFICATION 

2 MODEL/SERIES TYPE NUMBER AND MANUAL TI' 

8 FACE NUM~ER 

4 DATE OF ISSUE 

5 DATE OF REVISION (IF APPLICABLE) 

8 TITLE OF ILLUSTRATION AND FIGURE NUMBER 

7 MANUAL IDENTIFICATION NUMBER 

(EXISTENCE AND LOCATION OPTIONAL] 

B COPYRIGHT INFORMATION [OPTIONAL) 

1-2 " 1991 General Aviation Manufacturers Association Issued: February, 1991 
CAP 

Each page must bear the date of the original issue until revised and, when revised, that of the latest 

revision, lnstead of using the actual date of issue on each page of an original issue of a Document, 

the words 'original issue' may be used. In such a case, the Tile Page and the Table of Contents 

pages preceding each section of the Document must bear the actual date of issue following the 

words "original issue'. 

On pages requiring folding, make the fdd in a manner that permits the page number to be visible. 

Except as provided below, identify a normal Mank page within a page Mock (other than the back 

of a foldout page) with a phrase such as This page intentionally ManK. 

lnstead of printing This page intentionally ManK on Mank pages, the Document producer may use 

dual page numbering on pages preceding or following a Mank page. For example: 3-9 (3-10 Mank) 

or (3-9 blank/3-10). 

In the event a page must be added after the initial printing, use the number of the preceding page 

with a letter suffix added for the added page(s) (e.g., Page 1-64 1-6B, etc.). 

Text may be prepared in one or two columns with or without justification. Warnings, cautions and 

notes may be used to highlight or emphasize important points. Print all pages except wiring 

diagrams and foldouts on both sides. Start each section on a right-hand page. The manufacturer's 

masthead, publication title, airplane model, and issue or revision date must appear on all pages of 

loose-leaf Documents that have text, illustrations, figures or tables . 

Tab Diers 

Separate each Section and Appendix of a loose-leaf Document with a plasticized tab divider. 

Stagger the tab dividers and label them with section numbers or titles, or both. Separation of 

sections in permanently bound CAPS is not required. 

6. IdentifLing Revised Material 

Identify revisions, additions and deletions by a vertical black line along the outside of the page (or 

the column side opposite the gutter on two column pages) opposite only that portion of the printed 

matter that was changed. ldentrfy a revision to an illustration with a black vertical line in the left 

margin opposite the revised portion or use a "pointing hand" ( rp ). Show the date of the revision 

on each revised page. See Figure 1-1. 

Issued: February, 1991 

1-3 

1991 General Aviation Manufacturers Association 
THIS PAGE INTENTIONALLY BLANK 
CAP 

SECTION II - CONTINUING AIRWORTHINESS 

PROGRAM DOCUMENT PRESENTATlON 

1. Contents 

A Continuing Airworthiness Program lnspection Document contains the following information: 

Cover (optional). 

Tie Page. 

Preface (optional if necessary information is covered in the Objectives). 

List of Effective Pages. 

Record of Revisions. (Optional if information is provided elsewhere.) 

Table of Contents. 

Applicability. 

Objectives (optional if necessary information is covered in the Preface). 

Technical Document Reference. 

List of Continuing Airworthiness Program lnspections. 

Continuing Airworthiness Program lnspections (in Chapter Number order). 

A. Cover. 

(1) The cover title is Continuing Airworthiness Program lnspection Document for (list 

airplane names or models, or both, or the components). 

(2) In the alternative, the acronym CAP may be used (with the airplane model or 

component names). 

(3) Other information may be displayed on the cover. See Figure 3-1. 

B. Title Page. 

The Title Page contains the following information: 

Issued: February, 1991 

2- 1 

@ 1991 General Aviation Manufacturers Association 
CAP 

(1) The title, Continuing Airworthiness Program Inspection Document or the acronym 

CAP. 

(2) The airplane model name or description or the components covered. 

(3) The manufacturer's masthead or logo. 

(4) A statement conveying the intent of the following example: 

"The primary document containing the procedures for the continuing airworthiness 

of an airplane is the airplane's maintenance manual (instructions for Continuing 

Airworthiness). A document prepared in accord with this Specification 

supplements, and is designed for use with, that maintenance manual." 

(5) The effective date and revision number and date if applicable. 

(6) The manufacturer's address. 

(7) The part number, if applicable. 

Additional information, such as GAMA membership identification, copyright notice, etc., may 

be included. Format and layout is to be determined by the CAP producer, recognizing that 

it is desirable that the format and layout be similar to the producer's existing documents. 

NOTE: Back of the Title Page should be left blank except for items such as a 

Manufacturer's logo. 

See Figure 3-2 

C. Preface (optional if necessary information is covered in the Objectives). 

The Preface contains the following information: 

(1) The reasons for establishing the CAP program (discussion of service history) and 

the underlying problems to be prevented by compliance with the specific CAP. 

(2) The relationship of the CAP to normal inspection programs for the product. 

NOTE: The Preface has been omitted in the sample CAP in Section Ill and the 

necessary information has been included in the Objectives. 

D. List of Effective Pages. 

(1) The List of Effective Pages is formatted to provide: 

(a) A Chapter/Section/Subject column. 

(b) A page number column. 

(c) A date column. 

(2) Revision instruction information (such as, 'Insert Latest Revised Pages; Destroy 

Superseded or Deleted Pages") or revision history information, or both, may also 

be included. 

See Figure 3-4. 

2-2 

@ 1991 General Aviation Manufacturers Association Issued: February, 1991 
CAP 

E. Record of Revisions. (Optional if information is provided elsewhere.) 

The Record of Revisions is formatted to provide: 

(1) A Revision Number column. 

(2) A Date Inserted column. 

(3) A Date Removed column (optional). 

(4) A Page Number column. 

See Figure 3-5. 

F. Table of Contents. 

The Table of Contents is formatted to provide: 

(1) A Title column. 

(2) A Page Number column. 

See Figure 3-6. 

G. Applicability. 

The Applicability Statement contains the following information, appropriately formatted: 

(1) A list of models or components affected, in a column on the left side of the page, 

and a list of corresponding seriallunit numbers (or other identifying information), 

in a corresponding column on the right side of the page. 

(2) Special information, such as exclusions or additions, in note form. 

The listed model or components and listed serials/units are to be cumulative for all 

inspections in the Continuing Airworthiness Program lnspection Document. This will allow 

the user to identify an affected airplane by examining one list rather than having40 check 

each individual Continuing Airworthiness Program's lnspection for applicability. 

See Figure 3-7. 

H. Objectives. 

The Objectives Statement contains the following information: 

(1) The relationship of the CAP to existing inspection programs and the manufacturer's 

objectives for the CAP. 

(2) Optional information including (but not limited to) the rationale utilized to select 

CAPS - how the CAP requirements were determined (discussions of service history, 

tests and analyses). 

Issued: February, 1991 

2-3 

1991 General Aviation Manufacturers Association 
CAP 

The manufacturer may establish procedures to provide feedback (from operators and 

maintenance facilities who comply with a CAP) on unairworthy conditions (whether covered 

or not covered by the CAP) that were discovered when complying. 

See Figures 3-8, -9, and -10. 

1. Technical Document Reference. 

The Technical Document Reference contains a listing of necessary service documents (e.g., 

service bulletins, service letters, service kits, etc.) and related information directly identified 

in a Continuing Airworthiness Program Inspection. Only service documents directly 

involved with a CAP need be listed, in order, with document number (i numbered), full title 

and date. Show a source for all listed documents. 

See Figure 3-12. 

J. Listing of Continuing Airworthiness Program Inspections. 

(1) The Listing of CAP lnspections contains all Continuing Airworthiness Program 

lnspections in the CAP, in numerical order by CAP inspection number, with full title, 

date, effectivrty and inspection compliance. See Figure 3-14. 

(2) In the alternative, a block diagram, showing only Continuing Airworthiness Program 

lnspection numbers and time blocks may be used. See Figure 3-15. 

K. Continuing Airworthiness Program Inspections. 

(1) Continuing Airworthiness Program lnspections usually consist of two pages: one 

text page (see Figure 3-16) and one illustration page (see Figure 3-17). 

(2) The Continuing Airworthiness Program lnspection contains the following sections, 

in order, from the top of the page to the bottom (except as noted), in bold face 

type or underscored: 

(a) CONTINUING AIRWORTHINESS PROGRAM INSPECTION NUMBER - in 

the upper right comer of the image area on the text page(s) and, 

optionally, on the illustration page(s). The Continuing Airworthiness 

Program lnspection number is also displayed at the bottom of the page 

and is the CAP section number (see Note). 

2-4 

1991 General Aviation Manufacturers Association Issued: February, 1991 
CAP 

NOTE: The Continuing Airworthiness Program lnspection number is determined as follows: 

I Subject Number - To be 

determined by manufacturer, but 

generally numerically increasing 

with the number of individual 

inspections within the 

chapter/section group. 

Chapter Number - Both digits determined by 

GAMA Specification No. 2 Numbering System. 

I Section Number - First digit determined by 

GAMA Specification No. 2 Numbering 

System. Second digit determined 

sequentially by the manufacturer. 

Issued: February, 1991 

TITLE - at the top of the text page, at the left margin. 

For example: FUSELAGE/WING ATTACHMENT INSPECTION. 

EFFECTIVITY - directly below the title; show both model and serial/unit 

numbers as applicable. Exceptions and additions are also noted here 

(such as "except airplanes incorporating Service Kit Number 999"). 

INSPECTION COMPLIANCE - directly to the right of the effectivity and near 

the right margin. Instructions regarding %henu an inspection is required, 

and if repetitiie, are located here. Also state if additional repetitive 

inspections are required based upon initial inspection results. 

PURPOSE - directly below the Effectivii and lnspection Compliance 

sections, extending from the left to the right margins. Any service history 

discussion is also located here. 

INSPECTION INSTRUCTIONS - directly below the Purpose section and 

extending from the left to the right margins. 

ACCESS/LOCATION - directly below the lnspection lnstructions section, 

extending from the left to the right margins. Access and location 

instructions are provided here unless obvious. 

For example: Remove wing attach fairings. 

SIGNIFICANT INSPECTION CONDITION (detectable crack size, wear limits, 

corrosion condition, etc.) - directly below the Access/Location section at 

2-5 

1991 General Aviation Manufacturers Association 
CAP 

the left margin. Specifies, for a crack inspection, the minimum size crack 

expected to be discovered or, if no minimum is defined, a statement to this 

effect. Specifies, for other inspection conditions, the wear limits, corrosion 

pit depth, etc. 

INSPECTION PROCEDURE - located directly below the Significant 

lnspection Condition section, extending from the left to the right margins. 

Sets forth the inspection procedure@) to be utilized, such as; magnetic 

particle, visual, etc., and may reference another document for the actual 

procedure, such as a nondestructive testing manual. 

REPAIR/MODIFICATION - located directly below the lnspection Procedure 

section, extending from the left to the right margins. Sets forth repair or 

modification instructions and may refer to a standard repair in another 

document or a special repair or modification defined elsewhere, such as 

in a service kit, service bulletin, etc. 

COMMENTS - located directly below the Repair/Modification section, 

extending from the left to the right margins. Additional information or 

instructions, such as "Report any cracks found to this manufacturef', are 

contained here. 

SECTION NUMBER, PAGE NUMBER AND PAGE DATE - as indicated in 

Figure 3-16 or optionally, as shown in Section I - Page Numbers and 

Dates. The Continuing Airworthiness Program lnspection number becomes 

the section number and defines its placement within the CAP. 

RECOMMENDED OR REQUIRED RETIREMENT TIMES OF LIFE LIMITED 

PARTS (if established) - on the right side of the page in an appropriate 

space. Use of the word CAUTION, with appropriate 10-point uppercase for 

the text, enclosed in a box, is recommended. Sets forth manufacturer 

recommended retirement times for parts or assemblies (using hours, cycles 

or another appropriate determinant) and FAA required retirement (removal 

from service) times for life limited parts or assemblies. 

2-6 

@ 1991 General Aviation Manufacturers Association Issued: February, 1991 
CAP 

SECTION 111 - SAMPLE CAP 

issued: June, 1990 

3- 1 " 1990 General Aviation Manufacturers Association 
THIS PAGE INTENTIONALLY BLANK 
CAP 

CONTINUING AIRWORTHINESS PROGRAM 

INSPECTION DOCUMENT (CAP) 

FOR 

Light Single Engine Aircraft 

Model XXX Series 

A ABC Aircraft Company 

CAP Cover 

Figure 3-1 

3-2 

1990 General Aviation Manufacturers Association Issued: June, 1990 
THIS PAGE INTENTIONALLY BLANK 
CAP 

CONTINUING AIRWORTHINESS PROGRAM 

INSPECTION DOCUMENT (CAP) 

LIGHT SINGLE ENGINE AIRCRAF-T 

MODEL XXX SERIES 

issued: June, 1990 

1st edition 

prepared and published by 

ABC AIRCRAFT COMPANY 

1234 Anystreet Drive 

Anytown, VA 99999 

(555) 555-5555 

This document provides supplemental i- to the applicable airplane 

maintenance manual(s). 

,7 Member of GAMA 

Copyright a 1990 by 

ABC Aircraft Company 

Anytown, VA 

MANUAL IDENTIFICATION NUMBER 

CAP Title Page 

Figure 3-2 

Issued: June, 1990 

3-3 

a 1990 General Aviation Manufacturers Association 
THIS PAGE INTENTIONALLY BLANK 

Figure 3-3 

3-4 

d; 1990 General Aviation Manufacturers Association 

CAP 

Issued: June. 1990 
CAP 

CAP ABC Model >03( 

LlST OF EFFECTIVE PAGES 

CHAPTER 

SECTION 

SUBJECT 

COVER 

TITLE PAGE 

LlST OF EFFECTIVE PAGES 

RECORD OF REVISIONS 

CONTENTS 

APPLICABILITY 

OBJECTIVES 

SECTION I - TECHNICAL DOCUMENT 

REFERENCE 

SECTION I1 - LISTING OF CONTINUING 

AIRWORTHINESS PROGRAM 

INSPECTIONS 

SECTION 111 - CONTINUING AIRWORTHINESS 

PROGRAM INSPECTION 

PAGE 

i 

ii 

iii 

iv 

v 

vi 

vii 

DATE 

Insert Latest Revised Pages 

Destroy Superseded or Deleted Pages 

Issued: June, 1990 

1 

0 1990 ABC krcraft Company 

List of Effective Pages 

Figure 34 

Issued: June, 1990 

3-5 " 1990 General Aviation Manufacturers Association 
CAP 

ABC Model XXX CAP 

RECORD OF REVISIONS 

ii 

o 1990 ABC Aircraft Company Issued: June, 1990 

Record of Revisions 

Figure 3-5 

3-6 " 1990 General Aviation Manufacturers Association Issued: June, 1990 
CAP 

ABC Model XXX 

USTOFEFFECTIVEPAGES ....................................................... i 

RECORDOFRMSIONS ......................................................... ii 

APPLICABILITY ............................................................... iv 

OBJECTIVE ............................................................... v 

SECTION I - TECHNICAL DOCUMENT REFERENCE .................................... 1-1 

MaintenanceManuals ................................................... 1-1 

Service Bulletins ....................................................... 1-1 

SECTION II - LISTING OF CONTINUING AIRWORTHINESS 

PROGRAM INSPECTIONS ............................................. 2-1 

Checklist ........................................................... 2-2 

SECTION 111 - CONTINUING AIRWORTHINESS PROGRAM 

INSPECTIONS .................................................. 3-1 

5340-03 - Fuseiage/Wing Attachment Fitting ................................. 31 

Figure 31 - Fuselage,Mng Attachment Fitting ................................ 3-2 

iii 

Issued: June, 1990 1990 ABC Aircraft Company 

Table of Contents 

Figure 3-6 

Issued: June, 1990 

3-7 " 1990 General Aviation Manufacturers Association 
a CAP 

ABC Model XXX CAP 

APPLICABILITY 

MODa 

XXX 

XXX 

XXXX 

XXXX 

XXX 

XXXX 

XXX-0001 THRU XXX-0577 

XXX-0001 THRU XXX-0275 

XXXX-0276 THRU XXXX-1700 

XXXX-0001 THRU XXXX-0647 

RERR TO NOTE 1 

XXX-57841 THRU XXX-58818 

XXX-0001 THRU XXX-0197 

NOTE 1: XXXMX)l thru -0617 except airplanes incorporating S1003:-XX 

N 

0 1990 ABC Aircraft Company Issued: June, 1990 

Applicabilrty Statement 

Figure 3-7 

3-8 " 1990 General Aviation Manufacturers Association Issued: June, 1990 
CAP 

CAP ABC Model XXX 

1. Introduction 

The Continuing Airworthiness Program Inspection Document (CAP) is inspection data that, 

when combined with the operator's existing maintenance program, will help maintain the 

structural integrity and continued airworthiness of the ABC XXX Series airplanes. 

Although the airplanes addressed in this document are out of production, ABC continues to 

support them as outlined in our stated company policies. The factory has maintained 

technical assistance and parts support within stated policies. Service leners and owner 

information have been made available as necessary to maintain the airworthiness of the fleet. 

ABC has utilized condition report inputs to ensure maintenance and inspection guidelines 

are adequate and current by issuing updated guidelines when appropriate. 

The airplanes were delivered with recommended inspection programs to keep them 

airworthy. Because of the varied missions the airplanes performed, type of care given, and 

age and utilization rates, ABC has determined, based on inspections, tests, and analyses, 

that it is necessary to provide additional inspection requirements to further ensure that the 

airplanes can continue to carry the design loads it was originally certified for. 

This CAP has been developed in accordance with guidelines in FA4 Advisory Circulars 91-56 

and 91-60. The CAP is not intended to change or replace any portion of the applicable 

airplane Maintenance Manual or Service Letters. 

Each Section, such as "Technical Document Reference", 'Listing of Continuing Airworthiness 

Program Inspections", etc., starts a new page numbering sequence. 

2. Objective 

A This CAP has been prepared with the intent to expand present inspection requirements as 

a further assurance of the ability of the airplane to perform within the limits of the original 

certification. The CAP will add confidence in using the airplane for its assigned mission. 

B. The CAP will address primary and secondary airframe components, and primary and 

secondary systems to accomplish the stated objective of continued airworthiness. 

C. To establish the basis for those items to be included, the following assumptions have been 

made. 

Issued: June, 1990 

v 

0 1990 ABC Aircraft Company 

Objectives Statement 

Figure 3-8 

Issued: June, 1990 

3-9 

1990 General Aviation Manufacturers Association 
CAP 

ABC Model XXX CAP 

(1) The airplane has been maintained in accordance with ABC recommendations or 

equivalent. 

(2) Wherever the CAP is directed to a specific part or component, W is implied that the 

inspection will include observation and evaluation of the surrounding area of parts 

and equipment. Any maintenance anomaly would subsequently be brought to the 

attention of both the owner and maintenance personnel. Any anomaly should be 

reported to ABC, through the Condition Reporting System, so that additions and/or 

revisions can be made to the CAP where deemed neceglary. 

(3) Airplanes modified by STC are not the responsibility of ABC. Any item affected by 

STCs in ABC Manuals or CAPS must be brought to the attention of the STC holder 

by the owner or maintenance organization in order to obtain FAA-approved 

guidelines for the inspection, repair, preservation, etc. of that item. 

3. Rationale Utilized to Select Inspection Items 

Service Experience. 

(1) Customer correspondence and sewice reports were reviewed during the section 

process for the critical inspection items. Some reports were used to select items that 

were similar in application, design and loading even though no failures have 

occurred. 

(2) High-time airplanes, disassembled for major overhaul, were inspected to assist in 

selecting inspection items. Other high-time airplanes' special Continuing 

Airworthiness Program Inspection results supplement these inspections. 

(3) The effects of corrosion have not been considered in the rationale in selecting 

inspection times or in the effects on the fatigue stresses. tt is very difficult to 

determ~ne the effects of corrosion but, as the reports from the CAP inspections are 

received, the inspection times will be adjusted for any severe problems. 

Testing. 

(1) A review of test results applicable to the design was made. The loading conditions 

together with the resulting margins of safety were evaluated. The resulting data were 

used to determine if the component should be considered for incorporation into the 

CAP. 

Analysis 

(1) Existing analyses were reviewed to identify components and areas that may have 

exhibited lower margins of safety. 

0 1990 ABC Aircraft Company Issued: June, 1990 

Objectives Statement (Continued) 

Figure 3-9 

3-10 

1990 General Aviation Manufacturers Association Issued: June. 1990 
CAP 

CAP ABC Model XXX 

For the CAP to be successful on a continuing basis, it is essential that a free flow of 

information exist between the operator, FAA and ABC Aircraft Company. The significant 

details of inspection resutts, repairsand modiffcations accomplished must be communicated 

to ABC Aircraft Company in order to assess the effectiveness of the recommended 

inspection procedures and time intervals. In some cases, extension of inspection 

frequencies may be possible if the data suggests that the onsat of fatigue problems occurs 

at a greater number of flight hours than initially predicted. 

Additionally, items not previously considered for inclusion in the CAP may be uncovered 

through operator inspections. These items will be evaluated by ABC and, if applicable to the 

airplane configurations concerned, will be added to the document for the benefit of all. 

A reporting system, consistent with the systems employed by ABC Service Organization, has 

been established and incorporated into this document. Copies of the appropriate forms and 

a description of the entries to be completed are available to you from an ABC dealer or 

Factory Customer Service Representative. 

- NOTE: This system does not supersede the normal channels of communication for items 

not covered by the CAP. 

The discrepancy report should include the following: 

Continuing Airworthiness Program lnspection Number 

Airplane Model and Serial Number 

Airplane Hours 

Title of Continuing Airworthiness Program Inspection 

Location and Description of the Damage 

How Detected 

The operator may use standard ABC Condition Report form@) or an equivalent containing 

the same information. 

Send all available data, including repairs, Polaroid photos, etc., to: 

Service Department 

Attn: CAP Program 

ABC Aircraft Company 

1234 Anystreet Drive 

Anytown. VA 99999 

vii 

Issued: June, 1990 0 1990 ABC Aircraft Company 

Objectives Statement (Continued) 

Figure 3-10 

Issued: June, 7990 

3-1 1 

" 1990 General Aviation Manufacturers Association 
THIS PAGE INTENTIONALLY BLANK 

CAP 

Intentionally Blank Page 

Figure 3-1 1 

3-1 2 

a 1990 General Aviation Manufacturers Association Issued: June, 1990 
CAP 

CAP ABC Model XXX 

SECTION I - TECHNICAL DOCUMENT REFERENCE 

MAINTENANCE MANUALS 

Hmkn m 

Model XXX Maintenance Manual 

SERVICE BULLETINS 

SBXXX-XX-X Wings - Main W~ng Spar Modification 

SBXXX-XX-X Stabilizers - Vertical Stabilizer Tip Rb Modification 

To obtain a Maintenance Manual for the Model XXX Serim alrplano and the listed Service Bulletins, writs 

to: 

Documents Department 

ABC Aircraft Company 

1234 Anystreet Drive 

Pnytown, VA 99999 

Issued: June, 1990 

1-1 

0 1990 ABC Aircraft Company 

TechnXxcal Document Reference 

Figure 3-1 2 

Issued: June, 1990 

3-1 3 

1990 General Aviation Manufacturers Association 
CAP 

THIS PAGE INTENTIONALLY BLANK 

Intentionally Blank Page 

Figure 3-13 

3-14 

1990 General Aviation Manufacturers Association issued: June. 1990 
CAP 

CAP ABC Model MM 

SECTION I1 - LISTING OF CONTINUING AIRWORTHINESS 

PROGRAM INSPECTIONS 

Continuing 

Airworthiness 

Program 

l nspection 

Number 

32-3001 

32-3002 

32-50-01 

32-50-02 

S1~1 

Issued: June, 1990 

Title 

Main Landing Gear Act 

Mounting Bolts 

Main Gear Downlock 

Actuator 

Nose Gear 

Turning Stop 

Nose Gear Steering 

Collar and Upper 

Pressurized Cabin 

Inspection 

Date 

7/28/89 

7/28/89 

6/28/89 

7/28/89 

7/28/89 

Effectivity 

1970 Model XXX Series 

&On 

Model XXX, )030: & 

XXXX (1970 thru 1986 

Models) 

Models XXX, XXX and 

XXX Series 

All Models XXX's and 

XXX's, 2157841 8 On 

Inspection 

Compliance 

l nitial Repeat 

500 Hrs. 500 Hrs. 

1OOO Hrs. 1000 Hrs. 

or Annual or Annual 

3000 Hrs. 1000 Hrs. 

3000 Hrs. 1000 Hrs. 

See 

32-5042 

5000 Hrs. 3000 Hrs. 

1990 ABC krcraft Company 

Listing of Continuing Airworthiness Program Inspections (List Form) 

Figure 3-14 

Issued: June, 1990 

3-1 5 

O 1990 General Aviation Manufacturers Association 
CAP 

ABC Model XXX CAP 

CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS 

CHECK LIST 

Continuing 

Airworthiness 

Program 500 Hrs. 1000 Hrs. 

Inspection 

Number 

32-3001 j Initial & Repeat I 

32-3002 1 I Initial & Repeat 

32-50-01 Repeat 

I I 

32-5002 1 I Repeat 

3000 Hrs. 

Initial 

Initial 

Repeat ___I Initial 

2-2 

0 1990 ABC Aircraft Company Issued: June, 1990 

Listing of Continuing Airworthiness Program Inspections (Block Form) 

Figure 3-15 

3-16 

@ 1990 General Aviation Manufacturers Association Issued: June, 1990 
CAP 

CAP BC Model XXX 

SECTION 111 - CONTINUING AIRWORTHINESS 

PROGRAM INSPECTIONS 

TlTE CONTINUING AIRWORTHINESS INSPECTION NUMBER: !S40-03 

Fuselagewing Attachment Fitting 

All XXX Series Aircraft - 1967 & On 

PURPOSE 

MTUL XXXX Hrs. or Annual 

REPEAT ~M.ahnd 

To check Fuselage/Wmg Attachment Fitting 

INSPECXlON INSTRUCTIONS 

1. Reference SEBXX and Item 534004 of this CAP. 

2. See Rgure on page 2. 

3. Refer to the appropriate manufacturer's Service Manual. 

Main spar wing attach fittings. - Remove wing attach fairings. Do not remove dowel pins 

unless required in complying with Continuing Airworthiness Inspection Number 53-4004. 

DETECTABLE CRACK SIZE 

,060 Inch. 

INSPECTlON PROCEDURE 

CAU11ON: 

REPLACE NUTS AND WASHERS 

IF REMOVED DURING 

INSPECTION. DO NOT REUSE. 

Visual 

Replacement. 

COMMENTS 

Report any cracks found to this manufacturer. 

534043 3-1 

Issued: June, 1990 0 1990 ABC Aircraft Company 

Continuing Airworthiness Program lnspection 

Figure 3-16 

issued: June, f 990 

3-1 7 

O 1990 General Aviation Manufacturers Association 
CAP 

FUSELAGE WlNG CARRY-THRU 

FORGING 

ABC Model XXX CAP 

Figure 3-1 - FuselagefWing Anachmn! Fmtng 

3-2 53-4003 

Q 1990 ABC krcrafi Company Issued: June, 1990 

Continuing Airworthiness Program Inspection 

NOTE 

REMOVE FILLETS AND INSPECT FUSELAGE-TO-WING 

ATTACHMENT AT EACH XXXX-HOUR INSPECTION. 

CHECK DOWEL PIN RETAINING HARDWARE, CARRYTHRU SPAR, AND WlNG FITTINGS THOROUGHLY. 

Figure 3-1 7 

3-1 8 " 1990 General Aviation Manufacturers Association Issued: June, 1990