# 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

Copynght Q 1 996 by GeneralAviation ManufacturersAssociation 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/O1 /84) Page No.

... 111 iv v ' 0- 1 0-2 0-3 0-4 0-5 0-7 0-8 0-9 0-1 0 0-1 1 1-1 1-2 1-3 1

-4 1-5 2-1 2-2 2-3 2-4 2-5 2-6 3- 1 3-2 3-3 3A-1 3A-2 4- 1 4-2 4-3 5-1 5-2 5-3 5-4 5-5 5-7 5-36 5-37 6-1 6-2 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 Figure2-1. Revised para. 2.5. Revised para. 2.7, 2.9. Revised para. 2.1 1,2.12 and Figure2-3. 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. 4.19 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. Revisedtile. 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
Revisedtitle. 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 (1Of1 8/96) Page No.

... II~ iv 3-2 4-2 5-6 7-2 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 airplaneshaving a certification basis includingFAR 23 through Amendment 23-44 except Commuter Category (Ref. FAR 23 Amendment23-34, Amendment23-39 orboth). 

# PREFACE This Spe%ication was developed by representatives of member companies of the General Aviation Manufacturers Associationfor use in preparing Pilot's OperatingHandbooks thata. Are of maximum usefulness 

### as an operating referencebook forpilots; b. Meet governmentregulatory 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 airplanesoriginally certificated at maximum 

### takeoffweights of 12,500pounds 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 (SeeFederal AviationRegulation 1.3). "Shall" isused 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 obligationto 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

# - graphicalor tabular. No other format is permissible. Which to use, graphicalortabular, is a choice completely up to the Handbook (airplane)producer.
When a right orprivilege is conferredupon the producerof a Handbook, the word "may" is used. When a right orprivilege is abridged, the words "may not" 

### are used. Except when a specific layout, style, format, 

### standard,etc., 

### is 

### required (orwhen 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 choiceishis.
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 Sectionstoprovide easieraccessto information that may be required in flight.

### The units used arethose which will be of most value to pilots. CalibratedAirspeed (GAS)

### isto 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 aspressure altitudeand temperature. The Specification contains little, if 

### any, new material or novel approaches. Basically, it is a guide to industry standardizationofproven concepts to be presented in a form most

### usefulto pilots. The Federal Aviation Administration has 

### reviewed this Specification and has 

### ".

. . determined that a 

### handbook that would meet the specificationwould 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 compliancewith this Specificationwill result in a high degree of standardizationof content and format for all aircrafttypes and this will lead to a level of safety 

### equal 

### to or higherthan 

### isrequired underFAR 23. 

## *

Note: This Specification refers to various FAA regulations. If the Specification 

### is being used to prepare a 

### Handbook for acceptanceby an airworthiness authority other than FAA, 

### the appropriateregulations of that airworthiness authority 

### may be substituted.

### CONTENTS Section 0 

### I
2
3
3A
4
5
6
7
8
9
10 

### Technical PublicationGuidance General Limitations Emergency Procedures Abnormal Procedures (Optional) Normal Procedures Performance Weight andBalance and Equipment List (ifapplicable) Descriptionofthe Airplaneandits Systems Handling, ServicingandMaintenance Supplements Safety and Operational Tips (Optional) AlphabeticalIndex (Optional)

### SECTION 0 

### TECHNICAL PUBLICATION GUIDANCE TABLE OF CONTENTS

Paragraph Page General



### ............................................................................ 0-1



### ........................................................................ CoverTitle 0-1



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



### ................................................................... 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 SchematicDiagram Symbols,Devices

### or Codes



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



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



### ............................................................................ 0-3



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



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



### ............................................. IdentifyingRevised Material 0-4



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



### .......................................................... Obtaining 

### Revisions 0-4 Supplements



### ...................................................................... 0-4

### INTENTIONALLY LEFT BLANK

### SECTION 0 

### TECHNICAL PUBLICATIONGUIDANCE
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 bepublished. 

### 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 shallbe prominently displayed on the cover or spine (or both) of the Handbook. 

### Other information may be displayedon 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 OperatingHandbook and FAA Approved Airplane Flight Manual" for all airplanes except those for which the airplane manufacturer elected to provide a separateFAA 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 commonairplanename, orboth. 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 airplaneat 

### 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 

### THEMATERIAL REQUIRED TO BE FURNISHED TO 

### THE PILOT BY 

### THE FEDERAL AUTION REGULATIONS AND ADDITIONAL INFORMATION PROVIDED BY 

### THE MANUFACTURER."
2. The manufacturer'sname.

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

### 0-1 Q 1996 General Aviation ManufacturersAssociation9. 

### A statement that the Handbook meets 

### GAMA Specification No. 1, SPECIFICATION FOR 

# mors OPERATING 

### HANDBOOK, dated (date ofthe Specificationto which the particular Handbook conforms). 10. The date of FAA approval and signature and title ofthe 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 Tableof Contents ofthe Section.
0.11 Page Identification 

### The page numbers in each section will 

### include the sectionnumber 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, suchas 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 mannerthat permits the page numberto be visible. Except as provided below, a normal blank page within apage block. otherthan 

### 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 (3-10blank) or (3-9 blank.3- 10).
In the event a page 

### must be added subsequentto the initial printing, the page shall 

### carry the number of the preceding page with a letter suffix 

### added. The addedpage(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 ofthe Handbook.
For easeof 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. (SeeFigure 0-3) All illustrations, figures and tables shall 

### be referenced in the text as figures or by title (orboth). 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 colorispermissible.



### 0-2 @ 1996 GeneralAviation Manufacturers Association Issued: February 15,1975 Revised: October 18,19960.17 Schematic Diagrams, General Schematicdiagrams may be used to indicate "flow" and to illustratethe 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 accompanyingtext, or both.


### On schematic diagramswith a largenumber of listed items, (e.g., an electrical schematic) the items shall be presented in a logical order, such 

### asthe sequence of the arrangementof the itemsin 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 Spacepermitting, legends shallbe spelled out within the diagram rather than abbreviated or keyed by numerals to 

### a list of legends at the bottom or on an adjacentpage. 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 SchematicDiagram Symbols, Devices orCodes 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 ManufacturersAssociation

### Section4 

# - Section5 

# - Section6 

# - Section7 

# - Section8 

# - Section9 

# - Section 10 

# - Normal Procedures Performance Weight &

### Balance/ Equipment List Airplane & 

### Systems Descriptions AirplaneHandling, 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 Orderand Numbering 

### The orderofpresentation ofthe subjectmatter of the paragraphs used in this Specif~cation shall 

### be followed in 

### each Handbook exceptwhen (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, Section7.1, 

### 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 appropriateto 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 outsideof 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

### ofRevisions 

### 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 approvingthe 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 ornote shall 

### be contained in each Handbookto 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 ManufacturersAssociation Issued: February 15,1975 Revised: October 18,1996Issued: February 15,1975 Revised: October 18,1996 

# PILOT'S OPERATING 

# HANDBOOK AND FAA 

# APPROVED AIRPLANE ELIGHT MANUAL

THIS HANDBOOK INCLUESTHE MATERIAL REWIRED TO BE FURNlSHWTO THE PLOT BY THE FEDERALAVlA TlON REGULATIONS AND ADDITIONAL INFORMATION PROW BYTHE MANUFACTURER,AW C013STmmS THE FAA APPROVED AIRPLANE RIGHT MANUAL.

This Hmdbookmeet8 GAMASpodfkrtion No. 1, SpecMcationtorPilot's Operating Handbook, huedFebruary 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 -01996 General Aviation ManufacturersAssociation

### INTENTIONALLY

### LEFT BLANK

0-6 O 1996 GeneralAviation Manufacturers Association Issued: February 15, 1975 Revised: October 18,1996ITEM 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 91996 GeneralAviation ManufacturersAssociationTatcim NDBmkr

Orlgh.lal issue or Date of Rarision

C 

### Figure 0-3 

### Suggested

### HorizontalPage Layout



### 0-8 Q 1996 General Aviation ManufacturersAssociation Issued: Febtuary 15,1975 Revised: October 18,1996PILOT'SOPERATlNG HANDBOOK LOG OF REVtSfONS

Description of Revision



### Figure 0-4 

### Suggested

### Logof Revisions I Page Number I

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

### 0

# - 9 Q 1996 General Aviation ManufacturersAssociationPage 

### i saction Number I Ssction Tils I I



### 0-10 Q 1996 GeneralAviation ManufacturersAacociation 

### Figure 0-5 

### Suggested Vertical 

### Schematic

issued: February 15,1975 Revised: -bar 18,1996Layout Fire0-6 Fuel System Schematic

Figure 0-6 Fuel System Schematic

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

### 0-11 (O 1996 GeneralAviation ManufacturersAsaociation

### SECTION 1 

### GENERAL TABLE OF CONTENTS paragraph Page



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



### .................................................................... 

# . Introduction 1 1



### ....................................................... 

# . Three View Drawings 1 1



### ................................................ RequiredDescriptiveData 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

.............................................................. SpecificLoadings 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. 

### ThreeView 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) OverallLength (d) Wheel Base Length (e) 

### Main Landing Gear Track Width (f) Maximum PropellerDiameter (g) PropellerGround Clearance (h) Minimum Turning Radius (i) Wing 

### Area Required DescriptiveData 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 applicableto the airplane.
1.13 Engine(s) (a) Number ofEngines (b) EngineManufacturer (c) Engine Model Number (d) Engine Type, forExample: Reciprocating Engines Normally aspiratedorTurbocharged Direct Drive or Geared Air orLiquid Cooled Horizontally Opposed or 

### Radial Number of Cylinders Displacement TurbopropellerEngines Single Shaft or Multiple Shaft CompressorStagesand Types Combustion ChamberType Turbine Stages and Type (e) Horsepower Ratings and Engine (or Propeller)Rotational Speed (1) Takeoff Power (2) Maximum Continuous Power (3) MaximumNormal 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) PropellerManufacturer (c) PropellerModel Number (d) Number ofBlades (e) Propeller Diameter (f) PropellerType. forExample: Fixed Pitch or Constant Speed Full Feathering Reversible Hydraulic orElectricallyActuated Pitch Range

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

### 1-1 Q 1996 GeneralAviation ManufacturersAssociation1.17 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 Recommendedfor Various Average 

### Air Temperature Ranges (c) Total Oil Capacity (d) Drain and Refill Quantity (e) Oil Quantity OperatingRange
1.21 Maximum Certificated Weights (a) Maximum

### Ramp Weight (if applicable) (b) Maximum Takeoff Weight (c) 

### Maximum Landing Weight (d) MaximumZero 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 Spacesand Entry Dimensions Baggage Spaceor Compartment (a) CompartmentWidth 

### (b) Compartment Length (c) Compartment Height (d) CompartmentVolume (e) Entry Width (Minimum) (f) Entry Height (Minimum) (g) Other dimensions useful in determining what may be loaded. 1.29 SpecificLoadings Wing and power loading, based on the Maximum Takeoff Weight of Paragraph 1.21(b) and the Takeoff HorsepowerRating of Paragraph 1. l3(e)(l) and the Wing 

### Area ofParagraph 139.
1.31 Symbols, Abbreviations and Terminology Define symbols, abbreviations and terminology necessary for the clearunderstanding and precise use of the information presented in various sections of the Handbook. Defmitions should emphasize operationalsignificance when possible. The following guidelines shall be applied: 1. Define 

### all abbreviationsused or referred to 

### in the Handbook. 2 Define any special terminologies used in the Handbook with emphasis on those which wuldbe 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 AviationRegulations. (a) General Airspeed TerminologyandSymbols
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 airspeedto the speed of sound. True Airspeed is the airspeed of an airplane relative to undisturbed 

### air which is the CAS correctedfor altitude, temperatureand compressibility



### 1-2 O 1996 General Aviation ManufacturersAssociation Issued: February 15, 1975 Revised:October 18,1996Maneuvering Speed is the maximum speed at which application of 

### full available aerodynamic control will not overstressthe airplane. Maximum Flap mended Speed is the highest speed permissible with wing flaps in a prescribed extendedposition. Mkrimum landing GearExtendedSpeed 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 

### canbe safely extended orretracted. 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 OperatingLimit Speed is the speed limitthat may not be deliberately exceededin 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 exceededat 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,forpilot training. Note: Vs, is predicated upon the maintenance of conservative controllabilitymargins 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) MeteorologicalTerminology


### 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.(1013.2mb); (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 abovethat 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 GeneralAviation 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 assumedto be zero. A@ 

### atmospheric pressure at field elevation. The wind velocities recorded as variables on the charts 

### of thisHandbook are to be understood asthe 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 particularairplane 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. Thepower (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 engineon the ground, as slowly 

### as possible, yet sufficient to 

### ensure satisfactory engine, engine accessory, and airplane operation with a minimum ofthrust. 

### The thrust 

### of the propeller directed opposite the usual direction, thereby producing a braking action. The absence of appreciable thrust, 

### in eitherdirection. (d) Engine ControlsandInstruments 

### Include, 

### as applicable, definitions, descriptions or explanations of the following terms or components. The defintions, descriptions and explanationsprovided are examples. Those used in a particular Handbook should be appropriate forthat 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, orany combinationof 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 GeneralAviation ManufacturersAssociation 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 featherorunfeatherthe propeller. The exhaust gas temperature indicator, on piston engine powered airplanes, is the imtmment used to identify the lea.fuel flow mixtures forvariouspower 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 percentageor a pressure. Propeller The device that regulatesthe 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 isthe 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 definitionsnecessary for the pilot to use airplane performance information effectively. The following definitions should be included 

### as applicable. Climb Gradient

Demonstrated Crosswind Velocity

AccelerateStopDistance

AccelerateGo Distance The demonstrated ratio of the change in height during 

### a portion of a climb, to the horizontal distance traversed in the sametime 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 shouldbe stated.) The distance required to accelerate an airplaneto a specified speed and, 

### assuming failure of an engine at the instant that speed is attained, to bring the airplaneto a stop The distance required to accelerate an airplaneto a specifiedspeed 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 enrouteIFR 

### 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 Weightand

### Balance 

### Include defmitions of terms used in weight and balance descriptions and computations; such as: 

### Reference Datum

Station

Arm



### Moment

Centerof Gravity (C.G.)

C.G.

### Arm

C



### .G. Limits An imaginary 

### vertical plane from which all 

### horizontal distances are measured for balancepurposes. 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 ofthe 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 startofthe 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 GeneralAviation ManufacturersAssociation Issued: February 15, 1975 Revised: October 18,1996

### SECTION 2 

### LIMITATIONS
TABLE OF CONTENTS Page 2-1



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



### ............................................. Airspeed IndicatorMarkings 2-3



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



### ............ Power Plant Limitations (TurbopropellerEngines) 2-4



### ................................. MiscellanwusInstrument MarKings 2-5



### ................................................................... WeightLimits 2-5



### ................................................ Centerof Gravity Limits 2-5



### ............................................................... ManeuverLimits 2-6



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



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

............................................... 

### Kinds of Operations Limits 2-6 Fuel Limitations

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

................................................. Climb ConditionLimits 2-6



### .................................. Maximum OperationAltitude Limit 2-6



### ......................................... Outside 

### Air Temperature Limit 2-6

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



### ................................... Maximum Passenger SeatingLimit 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 OperatingHandbook shall contain only those limitations required by regulation or necessary for safe operation of the airplane and approvedby 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 differfrom 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 GeneralAviation ManufacturersAssociatiinI Maneuvering Speed VA(Knots) Maximum Flap Extended Speed 

# 1 I vm(Know MaximumLanding 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 SpeedLimit 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 abovethis speed. (Specify flap setting) Do not exceed this speed with a givenflap setting.
Do not extend orretract landing gear above this speed

Do not exceedthis speedwith landing gear ex%ended.

This isthe minimumflight speed at which the airplaneis directionally and laterally controllable, determined

### in accordance with the Federal AviationRegulations. Do not exceedthis airspeed or Mach Number in 

### any operation.

Do not exceed this speed orMach Number 

### in any operation.

Do not exceed this speed orMach Number except in smooth 

### air and then only with caution.



### Figure 2-1 

### Airspeed Limitations

Issued: February 15,1975 Revised: October 18,1996 O 1996 GeneralAviation Manufacturers Association2.5 

### Airspeed IndicatorMarkings 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)

Red Line 

# r

White Arc 

# I

Blue Line 

# I

Yellow Arc
Red Line

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

## I Full 

### Flap OperatingRange. 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. Operationsmustbe conductedwith caution and only in smooth 

### air.

1 

# IMaximum speedfor all operations 

# I

Figure 2-2 

### Airspeed IndicatorMarkings



### 2-3 O 1996 General Aviation ManufacturemAssociation

### 2.7 

### Power Plant Limitations (Reciprocating Engines) Provide the following powerplant limitations and data. 

### as applicable: (a) Number ofEngines (b) 

### Engine Manufacturer (c) EngineModel Number (d) Engine Operating Limits for Takeoff Power, Maximum Continuous Power, and Maximum Normal Operating Power, 

### as applicable. (e) Oil Pressure (Minimum andMaximum) (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 ofPropellers (k) 

### Propeller Manufacturer (I) 

### PropellerHub andBlade Model Numbers (m) PropellerDiameter(Minimum andMaximum) (n) Propeller Blade Angles at Specified Radius or Station (0) Propeller OperatingLimits (l)

### Rotational SpeedRestrictions 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 continuouspower less 

### thanthe 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 OperatingHandbook. 2.9 

### Powerplant Limitations (Turbine Engines) Provide the following powerplant limitations and data ,

### as applicable: (a) Number ofEngines (b) 

### EngineManufacturer (c) EngineModel Number (d) Engine Operating Limits shall be provided for thefollowing applicable operations: (I) 

### Takeoff (2) Maximum Continuous (3) Maximum Climb (4) 

### Maximum Cruise (5) Normal Cruise (6) Idle (Flight andlorGround) (7) 

### MaximumReverse (8) 

### Acceleration (9) 

### starting (10) 

### Other (e) Operating Limits associated with the type 

### of Operation specifiedby (d) above, may include: (I) 

### MaximumPower Indication (Torque, Shaft Horsepower) (2) Maximum Shaft Rotational Speed (3) Maximum Gas Temperature (4) 

### Maximum Time for SpecifiedOperation (5) Maximum Oil 

### Temperature (6) Other (f) 

### Oil Pressure (Minimum andMaximum) (g) Fuel Pressure (Minimum and Maximum) (h) 

### Other (Such

### as GeneratororAlternatorLimits) (i) 

### Fuel Grade or Specification and Approved Fuel Additives (Preferred and alternate, with any Limitationson use of Aviation Gasoline) (j) 

### Oil Grade or Specification and Approved Oil Additives (k) 

### Number ofPropellers (1) PropellerManufacturer (m) PropellerHub and Blade Model Numbers 

### (n) Propeller Diameter(Minimum andMaximum) (0) PropellerBlade Angles and Specified Radius or Station @) 

### PropellerOperatingLimits (l)

### Rotational SpeedRestrictions



### 2-4 Q 1996 GeneralAviation ManufacturersAssociation Issued: February 15,1975 Revised:October 18, 19962.11 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

- - 

# IOTHER (As Generator) I 

## I I 

## I 

# I

Figure 2-3 Power Plant Instrument Markings Arc CAUTIO N RANGE

2.12 MiscellaneousInstrument Markings Provide limitations and markings for miscellaneous instruments, such 

### as a pneumaticpressure 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 shallbe 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 followingweights 

### 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 AllowableForward 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 fromMinimum to 

### Maximum Takeoff Weight, landing gear extended, and shall include the followingsupporting information: (a) Guidance 

### as to the proper method of interpolating tabular statementsof the center of 

### gravity limits forvarious weights (b) A definitionof the Reference Datum relative to the airfr-amein 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 1996General Aviation Manufacturers Association 

### MAXIMUM LIMIT2.17 Maneuver Limits 

### The following information on maneuvers appropriateto the Airplane Category shall

### be given: (a) A Statement of Authorized Maneuvers and Appropriate

### Entry Speeds (b) 

### A Statementof 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 shallbe 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 TemperatureLimits 

### 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 SeatingLimits 

### Any limits on Maximum Passenger Seating, by number of passengers or specificrestrictions 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 limitationsnecessary for the safe operation of optional systems or equipment in this Section or in Section 9, 

### Supplements, or in both.
2.39 OtherLimitations 

### 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 Airspeedsfor 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 LandingEmergencies 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 abnormalitiesthat are not of emergency nature, or involve a potential emergency that may be deferred. may be included in this Section or in optional Section 34Abnormal Procedures. The incorporation of an Abnormal Procedures Sectionin 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 considerthe 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 

### aspossible. (b) The Emergency Procedures Section shall include at the beginning 

### a check list with regard to order of action when sequenceis 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 

### Airspeedsfor 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 eithermethod, 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: CHALLENGEOR RESPONSE OR 

### ITEM CONDITION Battery Switch OFF Generator OFF The check list should be limited to the minimum number of items determined to be essentialto 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 understandingof the reasons for actions in the check list. The amplified procedures may 

### also

Issued: February 15.1975 Revised: October 18,1996 

### 3-1 Q 1996General Aviation Manufacturers Associationinclude 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 subsequentaction(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 RecommendedAirspeed (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.
3.90Landing 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 DefectiveLanding Gear @) With Power, Landing GearRetracted @) Without Power, Landing GearRetracted 

## O Ditching, for 

### aircraft with extended overwater

### flight capability 

### (G) Approach and landingswith 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 InoperativeGo-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 (11) Environmental (12)Oxygen (13)IceProtection (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 Sectionfor 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 characteristicsand 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 arebased on the bestjudgment ofthe manufacturer.



### 3

# - 2 O 1996 GeneralAviation ManufacturersAssociation 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 spunby the manufacturer,if 

### such

### is the case. provided for emergencies peculiar to a particular airplanedesign, operating orhandliig characteristics

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

### 3-3 Q 1996 GeneralAviation ManufacturersAssociation

### 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 "EMERGENCYPROCEDURES" Section, is left to the Handbookproducer. 

### If an Abnormal Procedures Section 

### is provided, the subject matter and subject headings of this Sectionof 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 Specificationor may be arranged to suit a particular type or model of airplane. 

### In addition, Handbook writers shall considerthe 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 directlyusable aspossible. (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 featuresof each airplane.


### 3k 3 Airspeeds forAbnormal 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 CheckList. orboth.


### 3k5AbnormalProcedures

### CheckList 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 arrangedby "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 GeneralAviation ManufacturersAssociation

### 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 areferenceto Section 7, 

### Description of the airplane and Its System or Section 9, 

### Supplements.

3A-2 01996 General Aviation ManufacturerrAssociation 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) 

### IceProtection (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 

### Airspeedsfor 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 ofExternalPower 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



### ............................................................ MerLanding 4-2 

### Shutdown



### .................................................................4-2 

### Postflight ELT



### .........................................................4-2

.



### ........................................................ 4.11 

### Environment Systems 4-2



### .................................................. 4.13 

### OtherNormal Procedures 4.2



### ......................................................... 4.15 

### Noise Characteristics 4-2

................ 4.17 

### Proceduresfor Practice Demonstrationof 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 subjectheadings 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 subparagraphsof 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 directlyusable aspossible. (b) The Normal Procedures Section shall include, at the beginning. a check list, with regard to order of action, when sequenceis essential. (c) The Check List may be followed by amplified proceduresto 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 systemsor 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 EnginesRecommendedClimb 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 operationof 

### any system. The CheckList 

### 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 informationpertinent 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 GeneralAviation ManufacturersAssociationprocedureswould explainhow 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 particularhandling characteristics.For example, spin included 

### in this Section followingthe infonnation on recovery techniques may be included in this Section itemsin the Check List. of an acrobatic category airplaneHandbook.


### 4.9 Normal Procedures Except when inapplicable or inappropriate to the particular airplane model, Handbooks shall contain the recommended normal procedures for 

### the followingphases of 

### flight, in the order shown. (a) Preflight Inspection (b) Before Engine Starting (c) Use ofExtd Power (d) Engine Starting (e) Before Taxiing 

### (0 Taxiing (g) Before 

### Takeoff (h) 

### Takeoff 

## - Normal 

## - ShortField* 

# - SoftField* (i) Climb (i) Cruise (k) Descent (1) Before Landing (m)Landing 

## - Normal


## - ShortField* 

## - SoftField*


## - Balked (n) After Landing (0) Shutdown @) Postflight

### ELT 

## * Where such operationsare 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 operatorto minimize the noise impact of the airplane during operation at, or in the vicinity of, 

### airports. 4.17 

### Proceduresfor 

### 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 InoperativeSpeed.
The procedure shall specify that intentionally rendering one engine inoperative for the purpose of demonstrating, or training in, the recognition of 

### VMcA will be doneby starting at or above 

### Vs,then gradually reducing the speed (at approximately one knot per second) until either 

### VMcAor 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 differencebetween simulated and actualpower 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 GeneralAviation ManufacturersAssociation 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 andtips on fuel conservationmay 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 mustbe 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 GeneralAviation ManufacturersAssociation

### SECTION 

### 5 PERFORMANCE TABLE OF CONTENTS Paragraph Page



### .................................................................................. General



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



### .......................................... Identificationof Graphs & Tables



### ............................................................................. Limitations



### ...................................................................... Format Options ReaWiity of Graphs



### ............................................................



### ............................................................. Readability of Tables Associated Conditions



### ............................................................

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



### ............................................................................... Examples Location ofExamples


## .Associated Conditions and Technique

................................................................................... Weight Airspeeds



### ............................................................................... Distances



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



### ..................................... Wind Velocities



### ..................................................................... Fuel Density



### ........................................................................... Performance Formats 

### & Rules

................................................ 

### Minimum Performance Presentationsfor Single Engine

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

### Minimum Performance PresentationsforMulti-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 ofthe airplane.Thebasis 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 sampleflightplanning 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 Graphsor 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 ofthe 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 graphicalor tabular formats.
5.11 Readabilityof 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 integralpower of 10. 5.13 Readabity of Tables For tabular 

### data presentations, independent variables shallbe chosen 

### so that 

### hearinterpolation 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 SampleFlightPlanning 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 shallbe provided as applicable. (a) Power Settingand 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) wingFlaps (c) Cowl Flap Setting (d) Landing GearPosition

Issued: February 15.1975 Revised: October 18, 1996 

### 5-1 Q 1996 General Aviation ManufacturersAssociation

### (e) Environmental System Operation (f) 

### Ice Protection SystemOperation (g) Runway Precipitation,Slopeand SurfaceType (h) 

### LeariingInstructions
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 sequenceof 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 otheroccurrencesnot typical of actual situations. 

### (b) Present assumed example data in 

### the order in which it must be used in 

### the graph ortable. (c) Illustrate upon the face of the presentation graph or table, the successive entry of each assumed variable and the extraction ofthe end result. (d) 

### Demonstrate any necessary subsidiary computationswhich 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 ofExamples, 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 

### Airspeedvalues 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 airplaneperformance where altitude is 

### involved. No reference shall be made to density altitude. All 

### airplaneperformance 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 componentsin 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 

### Theformatsofperformance 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 Sectionareforguidance only. 5.37 Minimum Performance Presentationsfor 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 tabulatedperformance. (Figure 5- 

### 1) (b) Airspeed Calibration



### 5-2 Q 1996 GeneralAviation ManufacturersAssociation Issued: February 15,1975 Revised: October 18,1996

### Data shall 

### be presented as Calibrated Airspeed (CAS)versusIndicatedAirspeed (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 secondtable 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 distanceswere determined should be higher 

### than the power-off stall 

### speed for the same configuration. The chart should incorporate the limitsof 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 

### airtemperature and altitude at 

### maximum weight and

### maximumpower approved for climb. Climb speed(s) shouldbe 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 andDistance 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 shouldbe specified. (Figure 5-17 or 5-18) @) Cruise 

### Data shall

### bepresented as enginepower settings, (manifold pressure, engine or propeller speed, fuel flow or whatever parameters are required to establishpower) and true airspeedversus 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. Theformat shouldbe simpleto use forboth 

### preflight planning and inflight establishmentofpower. 3. The proper use of the data should be explained. (i) RangeProfdes 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 guidelinesshouldbe adheredto: 1. For start, 

### taxi and takeoff, allow 5 

### minutes offuel flow at takeoffpower. 2. For climb, assume a sea level takeoff and use the data presented on the time, fuel and distanceto climb chart.

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

### 5-3 91996 General AviationManufacturersAssodatiin3. 

### For all fuel loadings, the initial airplane weight shouldbe 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. Rangevalue shall 

### not includeparametersor 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) LandingDistance 

### Data shall 

### be presented as landing distance versus outside 

### airtemperature 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 PresentationsforMultiEngine Airplanes (a) introduction to Performance and Flight Planning An 

### actual trip, employing realistic or actual conditions, shallbe 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 shouldbe added if 

### applicable. (Figure 5-6 or 5-7) (e) Mmmum TakeofWeight("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 TakeofDistance 

### 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 obstacleheight may not be less than 

### 20% above the power-off stall speed@) forthe 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 ManufacturersAssociation 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-StopDistance 

### 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 1or 5-12) (h) Rate-of-Climb 

### Data shall 

### be presented as rate-of-climb versus outside air 

### temperature, altitude and weight at the maximumpower approved or as specifiedby the appropriate FAA requirements. Separate charts shallbe includedforthe following: 1. Rate-of-Climb-all engines operating with flaps set to the takeoffposition and landing gearretracted. 2 

### Rate-of-Climb-all engines operating with flaps setto the enrouteposition and landing gearretracted (If 

### applicable) 3 

### Rate-of-Climb-oneengine inoperative with flaps set to the enrouteposition 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-OneEngine 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 andDistance 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. (Figure5-17 

### 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 establishpower) and true 

### airspeedverslls 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 apower computer. 2. 

### The format shouldbe simpleto use forboth 

### preflight planning and inflight establishmentofpower. 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 shouldbe adheredto: 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 distanceto 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 shouldbe the maximum allowable. Reserve shall

### be computed as 45 

### minutes at the cxuise power to be used for the flight. The explanationinformation 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 GeneralAviation ManufacturersAssociationsettings 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 loadingsmay 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 shouldbe 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 settingfor holding. (Figure 5-23 or 5-24) (0) Time,Fuel &Distance toDescend 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~edcapabilities of the 

### aircraft and its iceprotection system. (b) Operations inIcing Conditions Data shall be presentedby general statements of allowances necessary while operating in icing conditionsorwith 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 areasof the airplane. (2) Data providing airspeed recommendations for operating with selected accumulations of ice orresidual ice shallbe presented. (3) Data providing airspeed recommendations and effects of boot operations prior to and duringthe 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 23.1419-2, 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 OperatingHandbook is encouraged.



### 5-6 0 1996 General Aviation ManufacturersAssociation 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 TakeoffWeight



### ..................................................... 5-8 Takeoff Distance 

### Graph



### .............................................................................. 5-9



### ............................................................................... Table 5-10 Accelerate-StopDistance



### .............................................................................. 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



### ............................................................... EnduranceProfde 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 GeneralAviation ManufacturersAssociation

### INTRODUCTIONTO TABtUTEDPERFORMANCE:
Tabulations of performance are presented in increments of temperature, altitude and any other variables involved. Perfonmince for a given set of conditionsmay be approximatedas foliows: Takeoff, climb, and landing

## - Entertables atthe next higher increment of altitude, temperature, weight and atzero wind.
Cruise Enter tables at next lower increment oftemperature, altitude and fuel loading;and the next higher incrementof weight if applicable.
To obtain exact performance values from tables, it is necessaryto interpolate betweenthe incremental values. The following is an excerpt from the Table for TakeoffDistances:

EXAMPLE
GIVEN: WEIGHT
OLJTSIDEAIR 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 SPEEDSAT 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 DISTANCETO 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 101KIM 50feet 118 KIM 25OC Ground Roll 3230 FEET Totalto Clear 5020 FEET 50' Obstacle
3966 FT INTERPOLATION METHOD: The example weight is 34% of the differencebetween 9.5 KNOTS 11,000 and 11,800 pounds. The example pressure altitude is 98% of the difference between 2000 and 4000feet The example temperatureis 50% ofthe difference between 20° and 30°6. Summary ofInterpolatedValues:

Takeoff Speeds Li-off 99 KIM 50 feet 116 KIAS Ground Roll 2818 FEET Totalto Clear 4416 FEET 50'Obstacle
CorrPetionfor Head Wind:

For a 9.5 Knot Headwind, decrease distancesby 7.6%. Ground RoU 2818-(7,676) (2818) =2604 feet Totalto Clear 44137.6%) (4416) =4080feet



### 5-8 Q 1996 General Aviatin ManufacturersAssociation 

### 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 INDICATEDAIR 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



### 5-10 O 1996 GeneralAviation ManufacturersAssociation Issued:February 15,1975 Revised: October 18,1996

### Figure 54

Issued:February 15.1975 Revised: Odober 18. 1996 

### 5-1

### 1 Q 1996 GeneralAviation ManufachrrersAssodabnALTIMETER CORRECTION.- NORMAL SYSTEM

FLAPS FULL INDICATED AIR SPEED 95 KlAS CORRECTION TO BE. ADDED -30 IT

1. ADD CORREClWNTO INDICATED ALTIMETER READING. 2 IASAND INDICATED ALTITUDE ASSUME ZERO INSTRUMENT ERROR.

COWDITION

FLAPSUP

Figure 5-5 FLAPS 1/3 FLAPS FULL



### 5-1 2 (B 1996 GeneralAviation ManufacturersAssodation CORRECTION TO BEADDED 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
-110



## - 1m
-115



## --


# -STALLSPEEDSCOWtRlollNOTES:1MAXlMUMALTITUDELOSSOURINGSTALLRECOVERYISAPPROXIMATELY800FEET2MAXIMUMNOSE DOWNPITCHATTITUDE ANDALTITUDELOSSDURINGRECOVERY FROMSINGLEENGINESTALLSPERFAR23.206AREAPPROXIMATELYlo0ANDmFEET.RESPECTIVELY3.LANDINGGEARPOSITIONHAS NOEPFECTONSTALLSPEED.'I10WEIGHT-POUNDSWEIOHT10.600LBSFLAPSlOOl6ANGLEOFBANK26'STALLSPEED77KNOTSIAS8QKNOTSCAS20304030ANGLEOFBANK-DEGREESSTALL SPEEDS

POWER IDLE LANDING GEAR UP OR DOWN WEIGHT 4800 LBS LANDING GEAR DOWN FLAPS 100% ANGLE OF BANK t6. STALL SPEED 58 KlAS 64 KCAS

1. MAXIMUMALTITUDE LOSS DURlNG STALL RECOVERY ISAPPROXIMATELY 800 FEET. 2 MAXIMUM NOSE WWN PlTW AlTrrUOEAND ALTITUDE LOSS DURING RECOVERY FROM SINGLE ENGINESTALLSARE APPROXIMATELY

### lo0ANDZOal FEET, RESPECTIVELY 3. LANDING GEAR POSITIONHAS NO EFFECT ON STALL SPEEDS.



### Figure 5-7



### 5-1 4 Q 1996GeneralAviation ManufacturersAssod?tion I WEIGHT LBS

42iao

Issued: Febnrary 15,1975 Revised: Odober 18,1996 CONDITION

FLAPSUP FLAPS 11‘3 FLAPSFULL 2 STALL SPEEDS % KNOTS ANGLE OF BANK 

# - 60" IAS 85 98 

### *5" 0"

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

MAXIMUMWEIGHT- POUNDS



### Figure

### 5-8

Issued: Febntary 15,1975 Revised: Odober 18,1996 

### 5-15 Q 1996 GeneralAviationManufeeturers lwocwmWWERFCACSLANDING(IEARRUNWAYTAKEOFFPOWERSETBEFOREBRAKERELEASE0%RETRACT AFTERLIFT-OFFPAVED. LEVEL.DRYSURFACETAKEOFFDISTANCE-0%FLAPSOAT26%PRESSUREALTITUDESO0FEETTAKEOFFWElOHT11276LMHEADWINDCOMrONEIlT9.6KNOTS(IROUNDROLL2620FEETTOTAL DISTANCEOVfRAWFOOTOBSTACLE4200FEETTAKEOFFSPEEDATLifT-WF98KIA5ATWFEET116KNOTSIABTAKEOFFDISTANCEASSOCIATED CONDITIONS:EXAMPLE:WERTAKEOFF POWERSETBEFORE BRAKERELEASEFLAPS0%LANDINGGEAR RETRACTED AFTERLIFTOFFRUNWAY PAVED.LEVEL. DRYSURFACEWEIGHT11276LBSOUTSIDEAIRTEMPERATURE16'~PRESSUREALTITUDE30MIFTHEADWINDCOMPONENT0.6KTSGROUNDROLL2804FTTOTALTOCLEARWFT.00s.4080FTTAKEOFFSPEEDATUR-OFF99KIAS60FEET116UIASNOTES:1.DECREASEDISTANCES4%FOREACH5KNOTS HEADWIND.FOROPERAllONWITHTAILWINDS UPTO10KNOTS, INCREASEDISTANCESBY8%FDREACH2.5KNOTS.2.WHEREMSTANCEVALUEHASBEENDELETED,CLIMBPERFORMANCEAFTERLl&-OFFISLESSTHAN-FTIMIN.RATE-OF-CLIMB16BASEDONALL ENGINESOPERATINOAtTAKWFPOWER.OURDOWNATTAKEOFFSPEED.3.IFTAKEOFF POWER SETWITHOUTBRAKESAPPLIED,THENDISTANCEAPPLYFR6MPOiNTWHEREFULLPOWERISATTAINED.TAKEOFFSPEED1KHOTS%IAS(':?1(IROUN$cTOTALORWNDF1a0cI44%TOTAL1OROUND1TOTAL1OROUNDITOTAL60FTOBSz10CLEARBOFTOBS3460401648307150ROLL23702720328037804676....210024162tMO34004070....TOCLEAR60FTOBIROLL10CLEARWFT09837006300....ACCELERATE-STOPDISTANCE-0%FLAPSASGQCIATEDWNOITIONS:MER1.TAKEOFFPOWERSETBEFORE BRAKE,-. .-..RELEASE2.BOTH ENGINESIDLEATENGINEFAILURESPEEDANDREVERSE OPERATINGENGINEFLAPSOnBRAKINGMAXIMUMRUNWAYPAVED,LEVEL,DRYSURFACEENGINEFAILUREWEEDEXAMPLE:KNOTS\ASnarunwPRESWt3EALTITUDEFEETWEIGHT11,!276LWHEADWINDCOMPOMNT0.6KNOTSaI..0000mIACCELERATE.STOPDISTAHCEBoo0rnENGINEFAILURESPEEDWOOfBETWKNOTSIASACCELERATE

# - 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 PRmUREALTITUDE S988 FT FAILURE SPEED AND REVERSE HEADWIND COMPONENT 9.5 KTS 

### ommffiENGINE. FLAPS 

### w BRAKlNG WlMW RUNWAY PAVED. LEVEL DRY SURFACE APPROXIMATION METHODACCELERATEDISTANCE 5870 FT ENGINE FAILURE SPEED 98 KlAS INTERPOUTIOFIMETHOD ACCELERATESTOP DISTANCE 5077 FT ENGINE FAILURE SPEED 98 KlAS NOTE:
1. DECREASE DISTANCES4% FOR EACH 6 KNOTS HEADWIND. FOR OPERATIONSWITH TAlLWINDS UP TO 10 KNOTS, INCREASE DISTANCES BY 696 FOR EACH 2.5 KNOTS 2. DISTANCES INCLUDE A FAILURE RECOGNITIONTIME OF 3 SHX)NDS.

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

LBS11500

11000

10000



### Figure 5-12



### 5-19 @ 1996 GeneralAviation ManufacturersAssociatkn 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-ONEENGINE INOPERATIVEASSOCIATEDCONDltlWPOWERMAXIMUMCONTINUOUSFLAPSOuLANDlNGGEARUPBLtEDAlRVALVESCLOSEDINOPERATIVEPROPELLERFEATHEREDBoo0OATP~ESS.ALTITUDEVO~FEEIMlDHT11.WLMRATEaCLIM#CLIMEWEEDOUTSIDEAIRTEMPERATUREOCWEIGHT-WNDSRATE4F-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 GeneralAviation ManufacturersAssociatiin

### SERVICE 

### CEILING 

# - ONE ENGINE lNOPERATIVE

WWFR ~XIUUW CONTINUOUS OATAT MEA roOc

.

## ---

## -
. . LANDING GEAR UP BLEEDAIR VALVE CLOSED IMPERATIVE PROPELLER FEATHERED ROUTE SEGMENTWEA t1,lrao FEET maw 1~us FLAPS UP NOTE: SERVICECEILINGISTHE PRESSUREALTITUDEWHERE AIRPLANE HAS CAP&BILITYOF CLIMBING W FTfWllNUTE WITHWE 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 GeneralAviation ManufacturersAssociation 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 1996General 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 CLIMBSPEED

KNOTS IAS
I 130 130

FEET 8800FEET TIMETO CLIMB (17 -3.6) 186MINUTES FUELTO CUMBt 180

## - 4% 137 LBS DISTANCETO 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 FUELTO CLIMB

# - POUNDS

DISTANCE TO CLIMB- NAUTICAL MILES 

### Figure 5-17



### 5

# - 24 8 1996 General Aviation ManufacturersAssociation 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. DISTANCESSHOWN ARE BASED ON ZERO WIND. 2. FOR TEMPERATURES ABOVE STANDARD, DECREASE RATE-OF-CLIMB40 FT/M1N FOR EACH 5QCABOVE STANDARD DAY TEMPERATURE FOR PARTICULAR ALTITUDE.

PRESSURE ALTITUDE FT SEA LEVEL CLIMB 

### SPEED WAS

90

90

90

90

88

84 WEIGHT LBS 3600 

### 3100 2600 

### 3MM 3100 

### 2600
3600 3100 2600 3600 3100 2600 3600 3100 2600 3600 3100 2600 RATE OF CLIMB FT/MIN

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 ManufacturersAssociation

### Figure 5-19



### 5

# - 26 (G4 1996 General Aviation ManufacturersAssociation Issued:February 15,1975 Revised: October 18,1996TIME, 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 LANDINGGEAR UP AIRPORT PRESSURE ALTITUDE 4MK1CT FLAPS 

### a CRUISE ALTITUDE 15000 FT INITIAL CLIMB WEIGHT 11600 LB6 TIME TO CLIMB 1123) 9 MIN FUELf0 CLIMB (141-37) 104 LBS DISFANCETO 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 1996GeneralAviation ManufacturersAssociation

### INTENTIONALLY 

### LEFT BLANK



### 5

# - 28 6 1996 GeneralAviation ManufacturersAssociation 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 91996 GeneralAviation ManuhcturersAssociation

### 5

# - 28B O 1996 GeneralAviation ManufacturersAssociation 

### 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 DESCENTWITH 46 MINUTES RESERVE FUELAT MAXIMUM RANGE POWER.

### 5 

# - 30 Q 1996 GeneralAviation ManufadurersAssociation 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. REQCftREDHOLDtNG 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 1996General Aviation ManufacturersAssociation

# TIME,

MSOCIATEDCONDITIONS: 

# FUEL,

POWER AS RECUREDTO DESCEND AT 1000 FT/MIN 

# AND DISTANCE TO

ALTfNDE DESCENTSPEED KNOTS IAS sim~ozepoo 20.m TO S.L.

LANOINGGEAR UP FLAPS 0% PROPELLER SPEED 1900RPM INITIALALTITUDE FINALALT%TUDE i7m FEET 5850 FEET
TIME TO DESCEND(17

## - 5.8) 11 MINUTES FUELTO DESCEND (142 -62) BO US DESCEMDISTANCEIS 

### - 8) 45 NM

0 50 100 1 So DESCENT DISTANCE

# - NAUTICALMILES 

### Figure 5-25



### 5 

# - 32 8 1996 GeneralAviation ManufacturersAssociation Issued: February 15,1975 Revised: October 18, $996

### TIME, FUEL, 

### AND DISTANCE TO 

### DESCEND

ASSOCIATED 

### CONDITIONS: EXAMPLE: POWER 

### AS REQ'D. FOR 

### 1000 

### FPM INITIALALTITUDE 

### 17,000FT 

## FLAPS UP FINALALTITUDE 5650 

### FT UND1NG GEAR 

### UP At 

### RSPEED 200 

### MAS TIME TO 

### DESCEND (17-6) 11 

### MlM 

### FUELTO 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 1996GeneralAviation ManufacturersAssociation 

### 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 GeneralAviation ManufacturersAssociation Issued: February 15,1975 Revised: October 18,1996LANDING 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 DISTANCES4% FOR EACH 5 KNOTS HEADWIND. FOR OPERATIONSWITH 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 

# I110 FTOBS 

# I 1 SO FT06s 

# 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 GeneralAviation ManufacturersAssociation Issued: February 15,1975 Revised:October 18,1996Issued: February 15, 1975 Revised:October 18, 1996 

### MULTI- ENGINE AIRPLANES IDENTIFICATIONOF GRAPHS OR TABLES

IN TYPICAL ORDER OFPRESENTATION INCLUDINGOPTIONAL ITEMS
ORDER 1 2 3 4 5 

## * 6 

## * 7 

## * 8

9 15 

## * 16

17 

## * 18

19
*20
*21
22 23
24 25 26 *27

28 29 *30

3 1 *32

33 *34

35 

### TITLE Introduction to Performance and Flight Planning Airspeed Calibration-Nod System Airspeed Calibration-Alternate System (If

### Applicable) AltimeterCorrection-Nod System AltimeterCorrection-Alternate System (If

### Applicable) Indicated Outside 

### Air TemperatureCorrection Fahrenheit to Celsius TemperatureConversion Terrain Clearance Limitations Stall Speeds TakeoffDistance 

### MinimumTakeoffDistance Accelerate-Stop Distance Accelerate-Go Distance Rate-of-Climb-All Engines Operating

(naps set to take-off position) Climb Gradient-OneEngineInoperative (Flaps set to take-offposition) Rate-of-Climb-All EnginesOperating

(naps set to emuteposition) Time, Fuel and Distanceto Climb Rate-of-Climb-OneEngineInoperative

(Flaps set to enrouteposition) Service Ceilings-OneEngineInoperative Rate-of-Climb-Balked Landing Cruise-AllEnginesOperating Cruise Speeds-Maximum Recommended

Cruise Power-All EnginesOperating Fuel and Tie Required Range Prof~le Range Payload Trade-Off-AllEngines Operating Endurance Profile CruisePerformance-OneEngine Inoperative Holding Time Pressurization Controller Setting forLanding Landing Distance *Optionalitemsmay be required by regulation for some airplane models.
Figure 5-30



### 5

# - 37 9 1996General Aviation ManufacturersAssociation

### SECTION 6



### WEIGHT AND BALANCE AND EQUIPMENTLIST (as applicable)

TABLE OF CONTENTS Paragraph 6.1 General 6.3 Airplane WeighingProcedure 6.5 

### Weight andBalance Record 6.7 

### Weight andBalanceDetermination forFlight 6.9 EquipmentList 

### Page

### SECTION 6 

### WEIGHT AND BALANCEAND 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 (usingjacking 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 shallbe 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. (SeeFigure 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 loadingform, the manufacturer may provide a device to be used to calculate weight and balance. Instructions for its use 

### shallbe provided. 

### 6.9 Equipment List The manufacturer shall provide 

### an equipment list 

### in 

### this Section, 

### in a separatedocument 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 installationby 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 differencebetween standard and optional equipment, if noted accordingly. All parts of an integral installationmap be combined into a single equipment list item if variation of weight or 

### arm is not significant. (seeFigure6-7.)


### 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 equipmentlist is A Weight and Moment Limit diagram shall be used to describethe c. g. limits. (SeeFigure 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 orrequired 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 1984GeneralAviation ManufacturersAssociation

### 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 atvarious places in 

### the airplane, each unit should be listed separately. (See Figure 6-7, Item 402)

6-2 O 1996GeneralAviation ManufacturersAssociation Issued: February 15,1975 Revised: October 18,1996AIRPLANE 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 fromthe reference datum

AIRPLANEAS WEIGHED. (rncludingfull oil and operatingfluids but no de fuel*)

Left Wing Right Wing POSITION 

# I I SCALE READING

.

### ---- I AIRPLANE TOTALAS WEIGHED (W) 

### 1 1 

# 1 SCALE ERROR

'Note: Normally weighed at factory without usablefuel. Figure 6-1 * NET WEIGHT

C G arm of a~rplane as we~ghed. (126.0)Wn 171.9 - W = inchesaft of referencedatum 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 GeneralAviation ManufacturersAssociation fuel drained) (6 Ibs per gallon) Optional Equipment (if applicable) BASIC EMPTY WEIGHT MOMENT (LBS

## - IN.) WEIGHT

(LBS)



### 1 CG ARM

ON-)WEIGHT AND BALANCE RECORD (Continuous History of Changes in Structure or EquipmentAffecting Weight and Balance) 

# I AIRPLANE MODEL 

# ( SERIAL NUMBER 

# I PAGENUMBERIssued: 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 01984 GeneralAviation ManufacturersAssociatiin

### WEIGHT AND BALANCE 

### LOADING FORM

Totals must be within approved weight and C G limits. It isthe responsibility of the airplane owner and the pilot to insure that the airplane is loaded property. The Basic Empty Weight C G is noted onthe 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 1996General 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. REGISTRATIONNO. DATE

ITEM 3CCUPANTS OR CARGO

:ABINET CONTENTS

'OTAL PAYLOAD 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, Ifthe airplane has been altered, refer to the Weight and Balance Recordfor 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)

MAINWlNG TANK FUEL LOADING

AUX. WlNG TANK FUEL LOADING

RAMP CONDITION {Sub-totail LESS FUEL FOR START & TAXI

TAKEOFF CONDITION

LESS FUEL TO DESTlNATION

LANDINGWEIGHT

i



### 6

# - 7 (B 1984GeneralAviation ManufacturersAssociationFUEL

BAGGAGE

WEIGHT 

# --pic

WEIGHT WING TANKS



### 6

# - 8 91996 GeneralAviation ManufacturersAssociation FORWARD REAR FS 170TO 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. 9FWAR ICENTER SUITS

REMOVED1 ARM 1W

Issued: February 15,1975 Revised: October 18,1996 AFT OF SPAR (CENTER 81 AFT SEATS REMOVED) ARM 146Format of

### EquipmentList:


### EQUIPMENTLIST


### Manufacturer Model


### SEXIAL

### NO. REGISTRATIONNO. 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 1984GeneralAviation ManufacturersAssociation

### SECTION 

### 7

DESCRIPTION OF ME AIRPLANE AND ITS SYSTEMS

TABLE OF CONTENTS Paragraph Page



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



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



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



### .............................................................. InstrumentPanel 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 PressurizationSystem 7-4



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

### Pitot Pressure Systems



### .......................................................7-4



### ..................................................... Static

### Pressure Systems 7-4 

### Vacuum orPneumatic 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



### ............................................................ WindshieldWipers 7-4

### SECTION 

### 7 DESCRIPTION OF 

### THE AIRPLANE AND ITS SYSTEMS
General This Section of the Pilot's OperatingHandbook 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 isprovided 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 abbreviationslisted in Section 1 are acceptable.
Reference to other books or to other sections of the 

### manual shouldbe kept to a minimum.
Where applicable the following topics should be included. Airframe Flight controls Ground control Wing flaps. divebrakes and spoiler systems Landing gear Baggage compartments lZlrplanetiedown provisions andjack points Seats. seat belts, and shoulderharnesses 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 Cabinpressurizationsystem oxygen system. Instrumentpanel Pitot pressure system Static pressure system Vacuum orpneumatic system Flight instruments Autopilot, flight director, and automatic devices in the control system Stall warningor 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 seatingarrangementsavailable.
7.5 Flight Controls (a) Describecontrol surfaces. (b) Describe operating mechanism-sketchesmay be provided. (c) Explaintrimming arrangements. (d) Explain any interconnect arrangement. (e) 

### If controls areboosted explainthe 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, switchesand controls found on the panel. (c) If an annunciatorpanel 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 GeneralAviation ManufacturersAssociation(b) Describe

### minimum radius of 

### turn for taxiing and groundhandling. 7.13 Wing Flaps, Dive Brake or Spoiler Systems (a) Describe aerodynamic surfaces. (b) Explainhow 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) Describeretractionmechanism if provided. 

### (c) Describe shock absorption system. (d) Describewheel brakes. (e) Explain emergency extension system. (f) Explain how warning systemfunctions. 7.17 Baggage Compartments (a) Explain locations. (b) Explain restrictions. (c) Describetie downprovisions 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 ShoulderHarnesses (a) Describehow 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 forgettingto 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. Gearreductionif 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 orpower control 2. Propellercontrol 3. Mixturecontrol 4. Cooling controls 5. Turbocharger controls 6. Friction lock (c) Describe the engineinstrumentation 1. Describebriefly 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) Describethe lubrication system including: 1. Typeof system 2. I.nsmmentation (f) Describeignition system (g) Describe the 

### airinduction 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 includingprovisions forpriming. (j) Describe the cooling system including cowl flaps. (k) Describe the engine starting system. (l) Describe simply the accessoriesincluding: 1. Oil pump 2. Fuelpumps



### 7

# - 2 8 1996 General Aviation Manufacturers Association Issued: February 15,1975 Revised:October 18,19963. 

### Hydraulicpump 4. 

### Airpump 5. 

### Tachometer 6. 

### Torque meter 7. 

### Electricalpower source 8. 

### Propellersyncbronizer 9. 

### Exhaust gas

### temperatureprobe 

### (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 describeit to a mechanic. It shouldnotbe a maintenanceprocedure.
7.27 Propeller 

### (a) Describe the propeller and its opeamtion if 

### pitch 

### canbe varied. (b) 

### Explain how thepropeller 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 explainthe 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 fuelventing system and consequence of allowing it to become plugged. 

### 01) Explain the fuel measurement system and discussneed for monitoring and calibrating. (i) 

### Explain restrictions,warnings and operating tips. 7.31 Hydraulic System 

### (a) Explain what itemsuse hydraulicpressure. (b) 

### Describetheprimary and auxiliary systems. (c) Provideone ormore schematicdiagrams of the system. (d) Describe controls and btxumentation of the system. (e) Discuss no& operation. (f) 

### Dixuss abnormal operation. (g) Explainrestrictions,warnings 

### and operatingtips.
7.33 

### Brake System 

### (a) Descriie thebrake system. (b) 

### Discuss how 

### to get 

### maximum braking and maximum

### life out ofthebrakes. 

### (c) Explain how to recognize impending problems andwhat 

### to do 

### if 

### malfunctions occur. 

### NOTE:At the manufachuds option, brake system description and discussion may be 

### coveredunderparagraph 7.15, 

### Landing 

### Gear.
7.35 Power Steering 

### If

### nose wheel power steeringisinstalled: 

### (a) Desmiethe system. (b) 

### Explainhow 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 circuitprotection. (d) Discuss 

### use of ground power units and battery charging. (e) Explain restrictions,warnings and operatingtips.
7.39 Lighting Systems 

### (a) Describe the various interior and exterior lighting systems. (b) 

### Explain how to troubleshoot malfunctions. (c) Discusshow to check and operate the systems. 7.41 AuxiliaryPower 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 ManufachrrerrAsmckWn

### (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 PressudtionSystem 

### If the airplaneis

### pded: (a) Describethe system. (b) 

### Fixplainhow to 

### operateit. (c) Explain how this 

### system ties

### in with the heating, ventilating, defrosting and air-conditioning systems. (d) Explainhow to recognize potential problems and handle emergencies.
7.47 

### Oxygen System (a) Describethe oxygen 

### systemif 

### one isofiered. (b) 

### Discuss restrictions orwarnings.
7.49 

### Pitot Pressure Systems (a) Describe thepitotpressure systems. (b) 

### Explain anti-icingprovisions, if 

### installed
7.51 

### Static Pressure Systems 

### (a) Describe the staticpressure systems. (b) 

### Explainthe alternate 

### static systemsif 

### 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 OrPneumatic 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 

### canbe checked. (d) Discuss how a failing system 

### can be recognized. (e) Discuss restrictionsand 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 operatethedevices. (c) 

### Discuss how to recognize a malfunction and how to handle the situation. 7.57 StallWdg 

### Or

### Angle ofAttack 

### System (a) 

### If either 

### of these devices is installed explain whetherit is

### required equipment. (b) 

### Explain the principleof operation. (c) 

### Explainhow to chedcthe 

### 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 forflightthrough 

### knownicing conditions. (b) 

### Descriiehow each item 1. 

### Operates, 2. 

### Canbe check84 3. 

### Canbe

### recognizedas malfunctioning, 4. 

### Mightbe corrected if

### malfunctioning. (c) 

### Explainresaictionsimposed on 

### each item.
7.61 

### Avionics (To be

### included at manufacturer's option) 

### (a) De~~lie items which 

### are standard and explain their

### functionand 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 GeneralAvtabon ManufacturersAswuabo . . 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 PreventiveMaintenance that may 

### be Accomplished



### ...................................................... by 

### a Certificated Pilot 8-1



### ..................................... Alterations or

### Repairs to Airplane 8-1



### ............................................................... GmundHandling 8.1



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



### ............................................................. Cleaningand 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'S43 and 91 or other applicableregulations) 

### as to who 

### may perform the required and manufacturer recommended inspections. 8.5 Preventive Maintenance

### That May 

### Be Accomplished By A CertificatedPilot (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 shouldrefer 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 contactedfor furtherinformation. (c) Includenote to statethat 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 AlterationsorRepairsto Airplane (a) Note that alterations or repairs to airplane must be accomplishedby licensedpersonnel. (b) Point out that the FAA should be contacted prior to 

### aqalterations on airplane to insure that airworthinessof the airplane is not violated.
8.9 Ground Handling Discuss the following items: 1. Towingprocedure 

### 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 shouldbe observed.

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

### 8-1 Q 1996General Aviation ManufacturersAssociation

### 8.13 Cleaning

### and Care 

### (a) Cleaning procedures for the following aircraft elements shouldbe 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 GeneralAviation ManufacturersAssociation (b) 

### Items to be included in the cleaning procedure shouldbe: 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 airplaneto service.

Issued: February 15,1975 Revised:October 18 1996

### SECTION 9



### TABLE OF CONTENTS SUPPLEMENTS



### ............................................................................. 9.1 

### General 9-1



### ............................................................. 9.3 

### SupplementScope 9-1



### ........................................................ 9.5 

### SupplementIssuance 9-1



### .............................................. 9.7 

### SupplementIdentification : 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 notprovided with the 

### standard airplane. 

### (b) Supplementsmay be prepared by the Handbook producer, supplied to the Handbook producerby the equipment supplierand 

### 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

### requiredby 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 certificatingor approving authority. 9.9 Page Numbering Supplement page numbers shall consist of a statement of the consecutive page numbers, such as "1 of 5", "2of 5", etc. 9.11 Structureof 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 OperatingHandbook 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 shallbe made. 9.5 Supplement Issuance All Supplementsfor 

### any particular airplane shall be issued by one or the other ofthe 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 availabilityof 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 GeneralAviation 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 statementto 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 shallbe made.



### 9-2 01996 General Aviation ManufacturersAssociation 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 OPERATIONALTIPS (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 FAApublications; (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 anotherperson. Acceptable child restraint seats are defined in publications such as Advisory Circular 91-62. 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 1996GeneralAviation ManufacturersAssociation

### ALPHABETICAL 

### ORDER

At 

### the option ofthe manufacturer,

### a con~prehensive alphabeticalindex may 

### be included followingthe last sectionin 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 ManufacturersAssociation 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

i ii iii N v 1-1 1

-2 1

-3 

## DATE March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991

March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991 March, 1991

I 

# ' 1991 General Aviation Manufacturers Association

### THIS 

### PAGE INTENTIONALLY BLANK

# CAP


# PREFACE
This Specification was developed by the General Aviation ManufacturersAssociation 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 informationto 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 minimizingthe 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 continuedairworthiness requirements for the manufacturer and owner/operator. Advisory Circular 91-56 

### provides "Guidelinesfor Development of ContinuingAirworthiness 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 ManufacturersTechnical Data, will aid in the preparation of a CAP for a specific airplane. It is intended that manufacturers retain and exercise reasonablejudgement and latitude in the content of their publicationswith 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 publicationstyle 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 Programfor 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 ManufacturersAssociation, Suite 801, 1400 K 

### Street, N.W., 

### Washington, D.C. 20005.

iv 

# " 1991 General Aviation ManufacturersAssociation 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 Explanationof 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 3-11

.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 ContinuingAirworthiness Program Inspections (List Form)

...... 

### 3-15 Figure 3-15

.Listing of ContinuingAirworthiness Program Inspections (Block Form)



### .... 

### 3-16 Figure 3-16

.ContinuingAirworthiness Program Inspection

....................... 

### 3-17 Figure 3-17

.ContinuingAirworthiness Program Inspection



### ....................... 

### 3-18

Issued: March. 1991 

### v 

# ' 1991 General Aviation Manufacturers AssociationTHIS 

### PAGE JNTENTlONALLY BLANK

# CAP

SECTION I

# - PHYSICAL 

# REQUIREMENTS

1. BbrferType 

### 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 (interimto 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 basictext in 10- or 12-pointtype. Use 14-point uppercaseboldfor the word

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

### CAmONand 10-point uppercase for the CAUTIONTEXT. Use 10-point uppercase boldfor 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 bearthe date of the original issue until revised and, when revised, that of the latest revision, lnstead of usingthe 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 printingThis 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).
Inthe 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 sectionon a right-hand page. The manufacturer's masthead, publicationtitle, 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 AssociationTHIS 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 primarydocument containingthe proceduresfor 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'saddress. (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, recognizingthat 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 compliancewith 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 ContinuingAirworthiness 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 relationshipof the CAP to existing inspection programs andthe manufacturer's objectives for the CAP. (2) Optional information including (but not limited to) the rationale utilized to select CAPS

## - howthe CAP requirementswere determined (discussionsof 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 maintenancefacilitieswho complywith 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 Referencecontainsa listingof necessary servicedocuments (e.g., service bulletins, service letters, service kits, etc.) and related informationdirectly identified in a Continuing Airworthiness Program Inspection. Only service documents directly involvedwith 

### 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 inthe CAP, in numerical order by CAP inspectionnumber,withfull title, date, effectivrty and inspection compliance. See Figure 3-14. (2) Inthe alternative, a blockdiagram, showing only ContinuingAirworthiness 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 ContinuingAirworthiness Program lnspectionnumber is determinedas 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

## - directlytothe right of the effectivityand 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, extendingfrom 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 INSPECTIONCONDITION (detectablecracksize, 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 expectedto be discovered or, if no minimum is defined, a statement to this effect. Specifies, for other inspectionconditions, the wear limits, corrosion pit depth, etc. INSPECTION PROCEDURE 

# - located directly below the Significant lnspection Condition section, extendingfrom 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 belowthe lnspectionProcedure 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 ContinuingAirworthiness Programlnspectionnumber 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-pointuppercasefor the text, enclosed in a box, is recommended. Sets forth manufacturer recommended retirement timesfor partsor 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 ManufacturersAssociationTHIS 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, 1990THIS 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 AssociationTHIS PAGE INTENTIONALLY BLANK

Figure 3-3



### 3-4
d; 1990 General Aviation ManufacturersAssociation 

# 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 RERRTO 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 inspectiondata that, when combined with the operator's existing maintenance program, will help maintain the structural integrityand 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 informationhave been made availableas necessaryto 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 requirementsto 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 FA4Advisory 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 requirementsas 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 accomplishthe stated objective of continued airworthiness.
C. To establishthe 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 reportedto ABC, through the Condition ReportingSystem, so that additions and/or revisions can be made to the CAP where deemed neceglary.
(3) Airplanes modified by STC are not the responsibilityof ABC. Any item affected by STCs in ABC Manuals or CAPSmust 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 Utilizedto Select Inspection Items
Service Experience. (1) Customer correspondence and sewice reports were reviewed during the section processfor 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 supplementthese 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 marginsof safety were evaluated. The resultingdata 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 ManufacturersAssociation 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 modiffcationsaccomplished must becommunicated 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 problemsoccurs 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 itemswill beevaluated byABC 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 systemsemployed byABC Service Organization,has been establishedand incorporated into this document. Copiesof 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 supersedethe 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 1990ABC Aircraft Company Objectives Statement (Continued) Figure 3-10

Issued: June, 7990 

### 3-11 

# " 1990 General Aviation Manufacturers AssociationTHIS PAGE INTENTIONALLY BLANK 

# CAP

Intentionally Blank Page Figure 3-11



### 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 ManufacturersAssociation

# CAP

THIS PAGE INTENTIONALLY BLANK

Intentionally Blank Page Figure 3-13



### 3-14 1990 General Aviation ManufacturersAssociation issued: June. 1990

# CAP

CAP ABC Model 

# MM

SECTION I1 

# - LISTING OF CONTINUING AIRWORTHINESS PROGRAM INSPECTIONS

Continuing Airworthiness Program lnspection Number

32-3001

32-3002

32-50-01

32-50-02

S1~1

Issued: June, 1990 Title
Main LandingGear 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 lnitial 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 

### 3-15
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 Initial 

# ___I

2-2
0 1990ABC 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 FuselagewingAttachment Fitting

All XXX Series Aircraft 

### - 1967 & On PURPOSE MTULXXXX Hrs. or Annual REPEAT ~M.ahnd

To check Fuselage/Wmg Attachment Fitting INSPECXlON INSTRUCTIONS

1. Reference SEBXXand 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.

### - Removewing attach fairings. Do not remove dowel pins unless required in complying with Continuing Airworthiness Inspection Number 53-4004. DETECTABLE CRACK SIZE
,060Inch. 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 1990ABC 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 3-17



### 3-1 

### 8 

# " 1990 General Aviation Manufacturers Association Issued: June, 1990