U. S. DEPARTMENT OF TRANSPORTATION : i ,-, ,-, ^ ^ 

OFFICE OF HEARINGS " ' ' '• ' ^ 

WASHINGTON, D.C. 

IN THE MATTER OF RECEIViP 

EMPIRE FLIGHT ACADEMY JUN " % W^ 

Respondent HEARING DOCKET 

FDMS NO. FAA-2010-0290 

HONORABLE RONNIE A. YODER B^^^ ' 1^ ^ "^^ ^ 13 V^ E 

CHIEF ADMINISTRATIVE LAW JUDGE 

Hearing Date: NONE ASSIGNED 

Hearing Location: NONE ASSIGNED 

RESPONDENTS' MOTION FOR PARTIAL SUMMARY JUDGMENT 

COMES NOW, Empire Flight Academy (hereinafter "Empire"), Respondent herein, by 

and through undersigned counsel, pursuant to Rule 13.218(f) of the Procedural Rules (14 

C.F.R. Part 13), and hereby moves for partial dismissal of the Complaint at Count III concerning 

regulatory allegations of 14 C.F.R. §§ 91.405(b), 91.407(a)(1), and 91.407(a)(2). 

The pleadings and other supporting documentation establish that there are no genuine 

issues of material fact to be resolved regarding the alleged violations in Count III of the Complaint. 

Therefore, Empire is entitled to judgment as a matter of law. In support thereof. Respondent states 

the following: 
PROCEDURAL HISTORY 

The Complaint filed in this matter on April 8,2011, alleges the following, in part: 

1. At all times mentioned herein, Empire Flight Academy was the operator of a Diamond 

DA-20 aircraft, identification number N383CA (hereinafter "the aircraft"). Complaint 

atlfl. 

2. On or about June 1,2009, Empire Flight Academy proceeded to operate the aircraft on 

a flight to Republic Airport, Farmingdale, NY (hereinafter "the June 1 flight"). 

Complaint at T|6. 

3. Count III of the Complaint alleges the following regulatory violations; 14 C.F.R. §§ 

91.405(b)', 91.407(a)(l)^ and 91.407(a)(2).^ 

' Section 91.405(b) states that each owner or operator of an aircraft shall ensure that maintenance 

personnel make appropriate entries in the aircraft maintenance records indicating the aircraft has 

been approved for return to service. 

^ Section 91.407(a)(1) states that no person may operate an aircraft that has undergone 

maintenance, preventative maintenance, rebuilding, or alteration unless it has been approved for 

return to service by a person authorized under Section 43.7 of the Federal Aviation Regulations. 

Section 43.7, states the following, in part: 

(b) The holder of a mechanic certificate or an inspection authorization may approve an 

aircraft, airframe, aircraft engine, propeller, appliance, or component part for return to 

service as provided in Part 65 of this chapter. 

^ Section 91.407(a)(1) states that no person may operate an aircraft that has undergone 

maintenance, preventative maintenance, rebuilding, or alteration unless the maintenance record 

entry required by Sections 43.9 or 43.11, as applicable, of the Federal Aviation Regulations has 

been made. 
ISSUE PRESENTED 

DOES A GENUINE ISSUE OF MATERIAL FACT EXISTS CONCERNING 

WHETHER MAINTENANCE PERSONNEL MADE AN APPROPRIATE ENTRY 

IN THE AIRCRAFT MAINTENANCE RECORDS INDICATING AIRCRAFT 

N383CA HAD BEEN APPROVED FOR RETURN TO SERVICE BY A PERSON 

AUTHORIZED UNDER SECTION 43.7 OF THE FEDERAL AVIATION 

REGULATIONS PRIOR TO THE FLIGHT ON JUNE 1,2009 PURSUANT TO 14 

C.F.R. § 91.405(B), § 91.407(A)(1); AND § 91.407(A)(2)? 

STANDARD FOR SUMMARY JUDGMENT 

A party seeking summary judgment must "demonstrate that there is no genuine issue of 

material fact in dispute and that the moving party is entitled to judgment as a matter of law." See, 

Accuracy In Media, Inc., v. National Transportation Safety Board, Civil Action No. 03-00024 

(CKK), 3 (D. D.C. 2006). 

As more fully described below, no genuine issue as to any material fact exists whether 

maintenance personnel made appropriate entries in the aircraft maintenance records indicating that 

aircraft N383CA had been approved for return to service prior to the flight on June 1, 2009, 

pursuant to 91.405(b), 91.407(a)(1), and 91.407(a)(2). Accordingly, since the pleadings and other 

supporting documentation establish that there are no genuine issues as to any material fact to be 

resolved concerning Count III of the Complaint, Empire is entitled to judgment as a matter of law. 

Therefore, Count III of the Complaint concerning the alleged violation of 14 C.F.R. §§ 

91.405(b), 91.407(a)(1), and 91.407(a)(2) must be dismissed with prejudice. 

MATERIAL FACTS NOT IN DISPUTE 

1. On or about April 18, 2009, Paul Masaracchia, Airframe & Powerplant (A&P) 

mechanic certificate number 104569374, performed a 100 hour inspection, including 

inspection of the landing gear of N383CA, at an aircraft total tachometer time of 932.1 
houris. See Exhibit A, Affidavit of Chief Inspector Carmine J. Colaluca, III at Exhibit 1, 

page 17, item #28. 

2. On or about April 18,2009, Paul Masaracchia, Airframe & Powerplant (A&P) 

mechanic certificate number 104569374, returned the aircraft to service following the 

100 hour inspection at an aircraft total tachometer time of 932.1 hours. Specifically, he 

determined that N383CA was "airworthy with respect to its maintenance condition." 

See Exhibit A at Exhibit 1 at page 40. 

3. On or about April 19,2009, Paul Masaracchia, Airframe & Powerplant (A&P) 

mechanic certificate number 104569374, made an aircraft maintenance record entry 

and returned the aircraft to service. Specifically, he stated that the aircraft was 

determined to be in "airworthy condition." See Exhibit A at Exhibit 2. 

4. Thereafter, on or about May 31,2009, Samer Elsayed, Airframe & Powerplant (A&P) 

mechanic certificate number 3245675, returned N383CA to service following a 50 

hour inspection at an aircraft total tachometer time of 982.2 hours. Specifically, Mr. 

Elsayed determined the aircraft to be in "airworthy condition." See Exhibit A at 

Exhibit 2. 

5. Prior to the flight on June 1, 2009, N383CA had been inspected and returned to service 

as airworthy by Paul Masaracchia, Airframe & Powerplant (A&P) mechanic certificate 

number 1045693744, pursuant to 14 C.F.R. §43.11 .^ See Exhibit A at Exhibits 1 & 2. 

* Section 43.11 states that the person approving or disapproving for return to service an aircraft, 

airframe, aircraft engine, propeller, appliance, or component part after any inspection performed in 

accordance with part 91,125, §135.411(a)(1), or §135.419 shall make an entry in the maintenance 

record of that equipment containing the following information: 
6. Prior to the flight on June 1,2009, N383CA had been inspected and returned to service 

as airworthy by Samer Elsayed, Airframe & Powerplant (A&P) mechanic certificate 

number 3245675 pursuant to 14 C.F.R. §43.11. See Exhibit A at Exhibit 2. 

ARGUMENT 

NO GENUINE ISSUE OF MATERIAL FACT EXISTS CONCERNING 

WHETHER MAINTENANCE PERSONNEL MADE AN APPROPRIATE ENTRY 

IN THE AIRCRAFT MAINTENANCE RECORDS TO INDICATE THAT N383CA 

HAD BEEN APPROVED FOR RETURN TO SERVICE BY A PERSON 

AUTHORIZED UNDER SECTION 43.7 OF THE FEDERAL AVIATION 

REGULATIONS PRIOR TO THE FLIGHT ON JUNE 1,2009. 

Although the regulatory violations alleged in Count III of the Complaint suggest that no 

aircraft maintenance entry exists returning N383CA to service prior to the flight on June 1,2009, 

no genuine issue of material fact exists concerning the regulatory charges. Accordingly, Empire 

Flight Academy is entitled to judgment as a matter of law concerning Count III of the Complaint 

(i.e., 14 C.F.R. §§ 91.405(b), 91.407(a)(1), and 91.407(a)(2)). 

(1) The type of inspection and a brief description of the extent of the inspection. 

(2) The date of the inspection and aircraft total time in service. 

(3) The signature, the certificate number, and kind of certificate held by the person 

approving or disapproving for return to service the aircraft, airframe, aircraft engine, 

propeller, appliance, component part, or portions thereof 

(4) Except for progressive inspections, if the aircraft is foimd to be airworthy and approved 

for return to service, the following or a similarly worded statement—"I certify that this 

aircraft has been inspected in accordance with (insert type) inspection and was determined 

to be in airworthy condition." 
Rule 13.218(f), which governs motions for decision, indicates the documents that may 

be considered by the law judge in ruling on a party's motion for decision. The Rule provides as 

follows: 

The administrative law judge shall grant a party's motion for decision if the pleadings, 

depositions, answers to interrogatories, admissions, matters that the adminisfrative law 

judge has officially noticed, or evidence introduced during the hearing show that there is 

no genuine issue of material fact and that the party making the motion is entitled to a 

decision as a matter of law. 

14 C.F.R. 13.218(f)(5); see also In the Matter of Horizon Air Industries, Inc., FAA Order No. 

96-24 (1996 FAA LEXIS 2058 (1996)). 

In American Airlines, Part 252 Enforcement, Orders 82-6-137, et al., 96 C.A.B. 114 

(1982), the Civil Aeronautics Board noted that: 

The Board has stated that in accordance with the Federal Rules of Civil Procedure, a party 

opposing a motion for summary judgment "may not rest upon the mere allegations or 

denials of [its] pleading, but [its] response.... must set forth specific facts showing that 

there is a genuine issue for trial". 

Citing, Aeromerica, Inc., Order 81-8-23, p.4. 

In the case at bar, the pleadings and evidence provided herewith (i.e., Exhibit A and 

attachments thereto) show that no genuine issue of material fact exists. Therefore, Empire is 

entitled to a decision as a matter of law concerning the existence of a return to service entry in the 

aircraft maintenance records prior to the flight on June 1,2009. Accordingly, Count III of the 

Complaint concerning the alleged violation of Sections 91.405(b), 91.407(a)(1), and 91.407(a)(2) 

must be dismissed as a matter of law. 

The Complainant rests upon the mere allegations of its pleading, without setting forth 

specific facts to show that there is a genuine issue for trial concerning the required maintenance 

record entries for the return to service of N383CA prior to the flight on June 1,2009. To the 
contrary, Respondent provides an affidavit attached hereto from Chief Inspector Carmine J. 

Colaluca (Exhibit A). Specifically, Chief Inspector Colaluca's uncontested testimony establishes 

that the necessary and required maintenance record entries for the return to service of N383CA 

existed prior to the flight on June 1,2009. Accordingly, the uncontested evidence establishes that 

there is no genuine issue as to any material fact to be resolved regarding the required maintenance 

record entry for the return to service of N383CA prior to the flight on June 1, 2009. 

Since the Complainant has not and caimot set forth specific facts showing that there is a 

genuine issue for trial concerning the alleged lack of a "return to service" maintenance record entry. 

Respondent is entitled to judgment as a matter of law. 

CONCLUSION 

Complainant has not and cannot set forth specific facts showing that there is a genuine 

issue for trial. 

WHEREFORE, Respondent respectfiilly requests that the Honorable Ronnie A. Yoder, 

Chief Adminisfrative Law Judge, dismiss Count III of the Complaint regarding 91.405(b), 

91.407(a)(1), and 91.407(a)(2) with prejudice. 

Dated: May 31,2011 

Respeo^:flb^ubmitted, 

JORY S. WJNTON, ESQ. 

ie Aviation Law Firm 

One ffleseapen Court, Suite 450 

Rock^HeTMD 20850 

Tel: (301) 294-8550 

Fax: (301) 294-2525 

Greg@AviationLawExperts.com 

Counsel for Respondent 
EXHIBIT A 
U. S. DEPARTMENT OF TRANSPORTATION 

OFFICE OF HEARINGS 

WASHINGTON, D.C. 

IN THE MATTER OF 

EMPIRE FLIGHT ACADEMY 

Respondent 

FDMS NO. FAA-2010-0290 

HONORABLE RONNIE A. YODER 

CHIEF ADMINISTRATIVE LAW JUDGE 

Hearing Date: NONE ASSIGNED 

Hearing Location: NONE ASSIGNED 

AFFIDAVIT OF C. JOHN COLALUCA, III 

1. I have personal knowledge of the following facts and make the following statements 

under the penalty of perjury, 

2. I have been the holder of an Airframe & Powerplant (A&P) mechanic certificate since 

1972. I have also been the holder of FAA Inspection Authorization (IA) for the past 30 

years. 

3. I am currently the Chief Inspector for a FAA Certified Repair Station. 

4. I have been recognized as an expert in general aviation maintenance by the Honorable 

William E. Fowler, Jr., Chief Adminisfrative Law Judge, the Honorable William R. 

Mullins, Administrative Law Judge, as well as the National Transportation Safety Board. 

5. I have reviewed portions of the FAA enforcement investigative report regarding the 

above-referenced matter. 

6. On or about April 18,2009, Paul Masaracchia, Airframe & Powerplant (A&P) mechanic 

certificate number 104569374, performed a 100 hour inspection, including inspection of 

the landing gear of N383CA, at an aircraft total tachometer time of 932.1 hours. See 

EXHIBIT 1 at page 17, item #28. 
7. On or about April 18, 2009, Paul Masaracchia, Airframe & Powerplant (A&P) mechanic 

certificate number 104569374, returned the aircraft to service following the 100 hour 

inspection at an aircraft total tachometer time of 932.1 hours. Specifically, he determined 

that N383CA was "airworthy with respect to its maintenance condition." See EXHIBIT 

1 at page 40. 

8. On or about April 19, 2009, Paul Masaracchia, Airframe & Powerplant (A&P) mechanic 

certificate number 104569374, made an aircraft maintenance record entry and returned 

the aircraft to service. Specifically, he stated that the aircraft was determined to be in 

"airworthy condition." See EXHIBIT 2. 

9. Thereafter, on or about May 31,2009, Samer Elsayed, Airframe & Powerplant (A&P) 

mechanic certificate number 3245675, returned N383CA to service following a 50 hour 

inspection at an aircraft total tachometer time of 982.2 hours. Specifically, Mr. Elsayed 

determined the aircraft to be in "airworthy condition." See EXHIBIT 2. 

10. Prior to the flight on June 1,2009, N383CA had been inspected and returned to service as 

airworthy by Paul Masaracchia, Airframe & Powerplant (A&P) mechanic certificate 

number 1045693744, pursuant to 14 C.F.R. §43.11. See EXHIBITS 1 & 2. 

11. Prior to the flight on June 1, 2009, N383CA had been inspected and returned to service as 

airworthy by Samer Elsayed, Airframe & Powerplant (A&P) mechanic certificate number 

3245675 pursuant to 14 C.F.R. §43.11. See EXHIBIT 2. 

12. Based upon my education, fraining, and experience, as well as my investigation of this 

matter, it is my opinion that: 

In accordance with 14 C.F.R. § 91.405(b), prior to the flight on June 1, 2009, 

maintenance persoimel made appropriate entries in the aircraft maintenance 

records for N383CA, indicating the aircraft had been approved for return to 

service. 

In accordance with § 91.407(a)(1), prior to the flight on June 1,2009, N383CA 

had been approved for return to service by a person authorized under Section 43.7 

of the Federal Aviation Regulations. 

In accordance v^dth § 91.407(a)(2), prior to the flight on June 1,2009, the 

maintenance record entry for N383CA required by Sections 43.9 or 43.11, as 

applicable, of the Federal Aviation Regulations had been made. 

13.1 am competent to testify as to the matters stated herein. 

C^H N COLALUCA, III 

Dated: May 27,2011 

EXHIBIT 1 
DA20-C1 AMM Diamond 

•/;•:-•::• > 

Time Limits and 

Maintenance Cliecks 

IVIAINTENANCE PRACTICES 

MAINTENANCE CHECKLIST DA20-C1 

1. General 

Enter the applicable data in the blocks below: 

S/N 

Date 

CcY > 

A: y r / 

Registration 

Engine hours, 

TTSNrrSMOH 

Check: 

Airplane 

Operating Hours. :. ^ 1 

\ ^ . 200, 1000, 6000, 

iinnual Inspection) 

At 25 hours time since new of an aircraft, inspect the items in the 100 hour column that DO NOT 

have an asterisk (*). Items that do have an asterisks beside may be initialed "N/A @ 25 hr" in the 

Initials column. 

2. Preparation 

Do the following items before you start the applicable check: 

T 

Inspection Items 

Interval (Flight Hours) 

(. 

50 / . 

7^ 

Q 

-iai> 

TT 

200 1000 6000 Initials. 

Before you do the inspection: 

Read the applicable Airworthiness 

Directives. 

For airplanes that are not U.S. Registered: 

Read the applicable Service Bulletins. 

Examine the Log Books. 

- Do a check of the Technical Records. 

Make sure that the mass and static 

moment for the ailerons, flaps, elevator 

and rudder are within the specified limits 

(Refer to Chapter 05-00) 

Clean the airplane fully. 

(Refer to Chapter 12-30). 

(b 

Not applicable at 25 hour inspection. 

Doc#DA201.C1 

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Time Limits and 

Maintenance Checks Diamond DA20-C1 AMM 

3. Engine Ground Test 

Do an engine ground test as follows (complete a copy of the Engine Ground Test Record as part of 

the engine ground test (Refer to Paragraph 7). 

Inspection Items 

Interval (Flight Hours) 

^ m j 200 1000 6000 Initials. 

WARNING: DO NOT LET PERSONS GO INTO THE DANGER AREA OF THE 

PROPELLER. PROPELLERS CAN CAUSE INJURY OR DEATH. 

WARNING: SET THE PARKING BRAKE TO ON. IF YOU DO NOT DO THIS, THE 

AIRPLANE CAN MOVE. THIS CAN CAUSE INJURY OR DEATH. 

1. 

2. 

3. 

4. 

Do an operational test of the parking brake. 

Set the parking brake to ON. 

Put the chocks against the airplane main 

wheels. 

Do an engine operational test. 

- For the engine run procedures refer to 

theDA20-C1 Flight Manual. 

- For the operational test refer to TCM 

Maintenance Manual Chapter 23. Refer 

to the operational checklist (Page 3) for 

difference in RPM settings. 

- Record the data in the checklist in 05-20-

00 para.7. Engine Ground Test Record. 

Do an functional test of the fuel shut-off 

valve, for correct operation. 

(Refer to Chapter 28-20). 

When the propeller stops rotating, set the 

ignition switch to the OFF position. Set the 

master switch to the OFF position. And set 

the fuel selector to the OFF position. 

0 

X 

X 

X 

f' 

X 

x 

X 

Page 6 

30 Apr 2008 05-20-00 Doc#DA201-C1 

Rev. 13 
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DA20.C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

4. Maintenance Checklist Zones 

Do the applicable checks in each of the zones that follow: 

A. Engine Compartment. 

All items performed, the findings, as well as their correction must be recorded in accordance with 

an approved procedures manual. Contact Diamond Aircraft if damages are determined which 

cannot be repaired in accordance with an approved procedures manual. 

Inspection Items 

Interval (Flight Hours) 

C ^ 200 1000 6000 Initials. 

WARNING: MAKE SURE THE EXHAUST SYSTEM IS COOL BEFORE YOU DO 

MAINTENANCE ON THE ENGINE. THE EXHAUST SYSTEM CAN 

BE HOT. THIS CAN CAUSE INJURY TO PERSONS. 

1. Remove the top and bottom cowlings. 

Examine the cowlings. Make sure that the 

fasteners are serviceable. Look for cracks 

and areas that have got too hot. 

T: (i> P-i 

WARNING: DO NOT GET OIL ON YOU. OIL CAN CAUSE SKIN DISEASE. 

WARNING: DO NOT GET FUEL ON YOU. FUEL CAN CAUSE SKIN DISEASE. 

DO NOT ALLOW FIRE NEAR FUEL. FIRE BURNS AND CAN 

CAUSE INJURY TO PEOPLE AND DAMAGE TO EQUIPMENT. 

2. 

3. 

Examine the engine for oil/fuel leaks. 

Remove the oil drain plug. Drain the engine 

oil into an approved container (with the 

engine warm). 

- Refer to the TCM Maintenance Manual 

Chapter 19. 

Install the drain plug. 

- Tighten the drain plug. Torque to 21.5-

23.8 Nm (190-210 in lbs). 

- Lock the drain plug with safety wire. 

Replace the oil filter. 

Refer to Chapter 79-00. 

Examine the lubrication system. 

- Refer to the TCM Maintenance Manual 

Chapter 19. 

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30 Apr 2008 
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Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

7. 

Inspection Items 

Cut open the used oil filter. Look for 

particles of metal. If the filter contains 

particles of metal, refer to the TCM 

Operators Manual. 

Interval (Flight Hours) 

50 100 

w^^ 

200 

x 

1000 

X 

6000 

X 

Initials. 

} f ^ 

CAUTION: YOU MUST USE ENGINE OILS THAT AGREE WITH THE APPLICABLE 

REVISION OF THE TELEDYNE CONTINENTAL MOTORS (TCM) 

SPECIFICATION MHS24 OR MHS27. FOR MORE INFORMATION SEE 

TCM SERVICE BULLETIN M87 REVISION 1 OR THE APPLICABLE 

REVISION. 

8. 

10. 

11. 

12. 

Fill the engine with new oil. 

- Refer to the TCM Maintenance Manual 

for oil specifications and quantity. 

Remove the spark plugs. 

- Examine the spark plugs. Look 

especially for damaged electrodes. 

- Clean the spark plugs (refer to spark 

plug manufacturers instructions). 

- Do a spark plug gap test (Refer to the 

manufacturers specified spark plug gap). 

Do a compression test with the engine warm 

and the throttle open. Refer to TCM 

Maintenance Manual Chapter 20. 

- Do the compression test on the four 

cylinders. 

G 

Record the compression test results. 

1 

: ^ [i ^ [32 ^t. 

Install the spark plugs. 

- Install the spark plugs with a new gasket. 

- Torque to 33-40 Nm (300-360 in lbs). 

- Refer to Teledyne Continental Motors 

Service Instructions for approved spark 

plugs. 

Do the 50 hour ignition system inspection. 

- Refer to TCM Maintenance Manual 

Chapter 12. 

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30 Apr 2008 05-20-00 

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V 

V 

Doc#DA201-C1 

Rev. 13 
DA20-C1 AMM Diamond^ Time Limits and 

Maintenance Checks 

Inspection Items 

Interval (Flight Hours) 

^ ; 200 1000 6000 Initials. 

13. 

14. 

15. 

16. 

17. 

18. 

19. 

Do the 100 hour ignition system inspection. 

- Refer to TCM Maintenance Manual 

Chapter 12. 

Do the 50 hour cylinder assembly inspection: 

- Refer to the TCM Maintenance Manual 

Chapter 20. 

Do the 100 hour cylinder assembly 

inspection: 

- Refer to the TCM Maintenance Manual 

Chapter 20. 

Do the 50 hour accessory case inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 18. 

Do the 100 hour accessory case inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 18. 

Do the 50 hour starter/starter drive 

inspection. 

- Refer to the TCM Maiptenance Manual 

Chapter 17. 

Do the 100 hour starter/starter drive 

inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 17. 

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Note: For the fuel injection system inspection the IDLE RPM setting for the 

IO-240-B engine installed in the DA20-C1 is 1000 ± 25 RPM. 

- Refer to the TCM Service Information Directive SID97-3C or latest approved revision 

20. 

21. 

22. 

Do the 50 hour fuel injection system 

inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 13 

Do the 100 hour fuel injection system 

inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 13 

Do the 50 hour induction system inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 14. 

© { ^ 

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^ 

X ^ ^ 

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Doc#DA201-C1 

Rev. 13 05-20-00 30 Apr 2008 
• ( 

........^,-^V: 

Time Limits and 

Maintenance Checks ^// ^ wJlaf X 

\ 

23. 

24. 

25. 

26. 

27. 

\on a. 

DA20-C1 AMM 

Interval (Flight Hours) 

Inspection Items Q^ ^ 

Do the 100 hour induction system 

inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 14, 

Do the 50 hour crankcase inspection. i 

- Refer to the TCM Maintenance Manual 

Chapter 21. 

Do the 100 hour crankcase inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 21. 1 

Do the 50 hour engine drive train inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 22. 

Do the 100 hour engine drive train 

inspection. 

- Refer to the TCM Maintenance Manual 

Chapter 22. 

,( 

% ^ 

( ^ 

^ 1 

y 

t>. 

X 

0 

200 

X 

X 

X 

X 

X 

1000 

X 

X 

X 

X • 

X 

6000 Initials. 

'" j ^ 

X 

"V 

X ^ 

X fvn 

X ' ^ ^ 

I 

WARNING: MAKE SURE THE EXHAUST SYSTEM IS COOL BEFORE YOU DO 

MAINTENANCE ON THE EX HAUST SYSTEM. THE EXHAUST 

SYSTEM CAN BE HOT. THIS CAN CAUSE INJURY TO PERSONS. 

28. 

29. 

Page 

30 A 

1 Examine the exhaust system. Look 

especially for cracks and heat damage. 

- Remove the flexible hoses from the heat 

exchanger. 

- Remove the heat exchanger shroud. 

- Do a check of the muffler. Look 

especially for cracks and leakage. 

- Install the heat exchanger shroud. 

- Install the flexible hoses to the heat 

exchanger. 

- Refer to Chapter 78-00. 

Examine the cabin heat system. 

- Remove the worm drive clamp from the 

flexible hose at the cabin-heat selectorvalve. 

- Disconnect the flexible hose from the 

cabin-heat selector-valve. 

- Examine the flexible hose for damage. 

pr°2008 05-20-0 0 

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X 

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DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

Inspection Items 

Interval (Flight Hours) 

(J^ (JOO, 200 1000 6000 Initials. 

30. 

31. 

32. 

33. 

34. 

35. 

36. 

37. 

38. 

39. 

40. 

41. 

42. 

43. 

- Examine the cabin-heat selector-valve. 

- Connect the flexible hose to the cabinheat selector-valve. 

- Install the worm drive clamp. 

Examine the engine baffles. Look especially 

for cracks and correct attachment. 

Examine the cowling seal on the firewall 

extension. 

Examine the electrical connections on the 

generator. 

Examine the generator mounting bracket. 

Look especially for cracks, the condition of 

the mounting bolts and the correct 

attachment of the mounting bolts. 

Do a test for correct adjustment of the 

generator belt. Refer to Chapter 24-30. 

Examine the air hoses. Look especially for 

signs of leakage and damage. Make sure 

the air hoses are correctly attached. 

Examine the cable ties and all electrical 

connectors. Pull lightly to make sure they 

are not loose 

Examine the battery area (aircraft with front 

mounted battery only). Look especially for 

cleanliness. 

Test starting vibrator battery (Refer to 

Chapter 74-00). 

Examine the drain pipes. Look especially for 

signs of chafing and damage. Make sure 

the drain pipes are clear. 

Examine the fuel hoses. Look especially for 

signs of leakage and damage. Make sure 

the fuel hoses are correctly attached. 

Examine the oil cooler. Look especially for 

leakage and damage. Make sure the 

cooling fins are not blocked. 

Replace the air filter. 

- Refer to Chapter 71-60. 

Examine the air filter 

-Refer to Chapter 71-60. 

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Doc # DA201-C1 

Rev. 13 05-20-00 Page 11 

30 Apr 2008 
^^•^^ A 

Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

Inspection Items 

Interval (Flight Hours) 

^ 200 1000 6000 Initials. 

44, 

45. 

46. 

47. 

48. 

49. 

50. 

51. 

52. 

53, 

Examine the air box 

- Refer to Chapter 71-60. 

Examine the engine starter relay. Look 

especially for correct attachment. 

Examine the throttle and mixture controls. 

- Make sure that the connection to the 

control lever is tight. 

- Make sure that the end fitting can turn in 

the control lever. 

- Examine the outer cables. Look 

especially for wear and for kinks. 

- On aircraft with a standard fuel pump 

only, lubricate the mixture control inner 

cable with a small amount of oil. Refer 

to Chapter 12-20. 

Clean the engine and engine compartment. 

- Refer to Chapter 12-30. 

Make sure there is no blockage of the 

engine oil separator. Long operation of the 

engine at low temperature with high air 

humidity, can cause blockage of the breather 

pipe. 

Remove and replace the engine mount 

hardware on the firewall. 

Replace all of the engine mount bolts. 

Examine the engine mounts not replaced. 

Look especially for: 

- Cracks or corrosion. 

- Correct attachment and condition of the 

mounting bolts. 

- Deterioration of the shock mounts. 

- Correct torque value (Refer to Chapter 

20-00, Section 4). 

Visually examine the forward firewall. 

Examine the condition of the paste fillet and 

fire paint over the edge of the fire shield on 

the front face of the firewall. Check for 

cracks, damage and disbond from the fire 

shield. 

Bleed the fuel system. 

(Refer to Chapter 73-00). 

k J 

0 

0 

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Page 12 

30 Apr 2008 05-20-00 Doc#DA201-C1 

Rev. 13 
{ f 

DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

inspection Items 

Interval (Flight Hours) 

200 1000 6000 Initials. 

Note: For the fuel injection system inspection the IDLE RPM setting for the 

1O-240-B engine installed in the DA20-C1 is 1000 ± 25 RPM. 

- Refer to the TCM Service Information Directive S1D97-3C or later approved revision. 

54. Do the fuel system check/adjustment. 

Refer to the TCM Maintenance Manual 

warning Chapter 6. 

D Th 

WARNING: DO NOT LET PERSONS GO INTO THE DANGER AREA OF THE 

PROPELLER. PROPELLERS CAN CAUSE INJURY OR DEATH. 

WARNING: YOU MUST MAKE SURE THAT THE ENGINE IS SAFE BEFORE 

YOU TURN THE PROPELLER. DISCONNECT THE SPARK PLUG 

LEADS. MAKE SURE THAT: 

- THE IGNITION SWITCH IS IN THE "OFF" POSITION. 

- THE "P" LEADS ARE GROUNDED. 

- THE THROTTLE IS SET TO "CLOSED". 

- THE MIXTURE CONTROL IS SET TO "LEAN CUT-OFF". 

WARNING: FAILURE TO COMPLY WITH THE FOLLOWING MAY RESULT IN 

THE LOSS OF THE PROPELLERI THE HUB OF A WOODEN 

PROPELLER WILL SHRINK OR EXPAND TO MATCH THE AMBIENT 

CONDITIONS. EXCESSIVE HUB SHRINKAGE, EESPECIALLY 

POSSIBLE DURING VERY COLD AND/OR DRY AMBIENT 

CONDITIONS CAN RESULT IN LOSS OF PROPELLER BOLT 

TORQUE (PRE-LOAD). THIS CAN ALLOW SLIGHT MOVEMENT 

RELATIVE TO THE DRIVE FLANGE, WHICH MAY RESULT IN 

DAMAGE TO THE PROPELLER AND/OR THE PROPELLER BOLTS, 

POSSIBLY EVEN LOSS OF THE PROPELLERI TO PREVENT THIS. 

PROPER INSTALLATION AND PERIODIC RE-TORQUING IN 

ACCORDANCE WITH ALL APPLICABLE MAINTENANCE 

INSTRUCTIONS IS NECESSARY. 

UNDER ALL CIRCUMSTANCES THE INSPECTION INTERVALS 

MUST NEVER EXCEED 50 HOURS. EXTREME CHANGES IN 

AMBIENT CONDITIONS (TEMPERATURE/HUMIDITY) MAY 

REQUIRE SHORTER INSPECTION INTERVALS. 

55. 

56. 

Remove and clean the spinner. Examine 

the spinner and backing plate for cracks. For 

Sensenich propeller W69EK-63 (3/8" bolt 

attachment) only. 

- Refer to Chapter 51. 

Examine the propeller extension. Inspect for 

cracks, dents and wear damage. Make sure 

that it is seated correctly. 

U P ^ 

Doc#DA201-C1 

Rev. 13 05-20-00 Page 13 

30 Apr 2008 
\-^. ^ 

Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

57, 

58. 

Inspection Items 

59. 

Check propeller attachment bolt 

torques. 

Refer to Chapter 61. 

For Sensenich propeller W69EK7-

63 or W69EK7-63G (7/16" bolt 

attachment) refer to the Sensenich 

W69EK7-CF Manual. 

For Sensenich propeller W69EK-63 

(3/8" bolt attachment) refer to the 

Sensenich W69EK-CF Manual. 

For Hoffmann propeller HO-14HM-175-

157 Refer to the Hoffmann Owner's 

Manual number E0110.74. 

Interval (Flight Hours) 

(M. 

50> 

'CL^ 

•1001 

^ 

200 1000 6000 Initials. 

fv 

CAUTION: IMPROPER TORQUE VALUES WILL BE OBTAINED BY MEASURING THE 

BREAKING TORQUE IN A LOOSENING DIRECTION. THE TORQUE 

SHOULD BE CHECKED IN A TIGHTENING DIRECTION AND ADJUSTED 

AS NEEDED. 

60. 

51 

Check blade tracking. Tracking must not 

exceed 1/8". 

- Refer to the Sensenich Document 

(W69EK-CF or W69EK7-CF) 

- Refer to The Hoffmann propeller 

Owner's Manual (number E 0110.74). 

Install new cotter pins (W69EK7-63 or 

W69EK7-63G propeller with castellated nuts 

only). 

Lockwire the attachment bolts in pairs 

(Hoffmann and W69EK-63 propeller) 

Install the spinner. 

- Refer to Chapter 61. 

Sensenich propeller only: 

Apply a non-silicon automotive type paste 

wax to the propeller blades. 

^ ; 

<2; 

Q 

0 

Q 

^ 

Note: Do not apply wax to the propeller hub area. 

Not applicable at 25 hour inspection 

1 Required at annual inspection for 

airplane maintenance done to FAR 91 

Page 14 

30 Apr 2008 05-20-00 Doc#DA201-C1 

Rev. 13 
f '•-

f r'\ 

DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

B. Front Fuselage 

All items performed, the findings, as well as their correction must be recorded in accordance with 

an approved procedures manual. Contact Diamond Aircraft if damages are determined which 

cannot be repaired in accordance with an approved procedures manual. 

Inspection Items 

Interval (Flight Hours) 

( M ) 

^ 

200 1000 6000 Initials. 

3. 

Examine the complete surface of the front 

fuselage. Look especially for damage 

(dents, cracks, holes, scratches and 

delamination). 

Examine the paint coat. 

Visually examine the condition of the paint. 

Look for chips, scratches, UV damage, and 

condition of fire-proof paint aft of lower cowl 

outlet. 

Inspect for cracks in the paint at the bonding 

seam down the centre line of the fuselage, 

upper and lower surfaces. 

Do a visual inspection and a tap test of the 

fuselage skin. 

- Inspect for disbonding between internal 

composite components and skin. 

Examine the composite structure around the 

entrance steps. Inspect especially for cracks 

or delaminations in the attachment area. 

Examine the canopy. Check the latching 

components for corrosion wear and damage. 

- Inspect the aft mount and rear hinge, the 

forward attaching points, the rubber 

stopper and the balance spring. 

Make sure the canopy locking mechanism 

will release. (Refer to Chapter 52-10). 

Visually examine the canopy frame. Check 

for delamination. scratches and cracks, 

especially around the fastener holes. 

Do the canopy latch force test. 

(Refer to Chapter 52-10). 

Examine the fuselage around the mounting 

hardware for the canopy latch. 

- Inspect for security of the mounting 

hardware. 

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Rev. 13 05-20-00 Page 15 

30 Apr 2008 
( 

Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

Inspection Items 

Interval (Flight Hours) 

^ 

200 1000 6000 Initials. 

9. 

10. 

11. 

12. 

13. 

14. 

15. 

16. 

17. 

18. 

19. 

20. 

21. 

22. 

23. 

- Inspect for cracks and delamination of 

the composite. 

Remove the wheel fairings. Look for cracks 

on the fairing mounts. 

(Refer to Chapter 32-40). 

Lift the airplane on jacks. 

(Refer to Chapter 07-10). 

Examine the tires. Look especially for cuts 

and wear. Measure the tire pressure. 

(Refer to Chapter 12-10). 

Examine the rims of the main and the nosewheel. Look especially for cracks. 

Examine the wheel bearings. Look 

especially for play, corrosion and irregular 

operation. 

Remove the main wheels. Clean and 

lubricate the bearings. 

(Refer to Chapter 12-20). 

Visually examine the condition of the axles. 

Look especially for cracks and corrosion. 

Visually examine the struts and shims in the 

outboard brackets. Check for the correct fit 

of the components. 

Remove, disassemble and clean the brake 

cylinders (4x) and calipers (2x). 

Replace the O-Rings and assemble the 

brake cylindei-s (4x) and calipers (2x). 

Examine the brake lining. Look especially 

for wear. 

Minimum thickness 3.0 mm (0.12 in) 

Examine the brake disks. Look especially 

for wear. 

Minimum thickness 3.8 mm (0.15 in) 

Install the main wheels. 

(Refer to Chapter 32-40), 

Remove the main landing-gear struts 

(Refer to Chapter 32-10), 

Examine the main landing gear, 

- Inspect for cracks and deformation, 

- Inspect the strut for distortion, corrosion 

and paint condition. 

Page 16 

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Doc#DA201-C1 

Rev.13 
c r 

DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

Inspection Items 

24. Measure the maximum deflection of the 

main landing-gear struts. 

Lay a straight rod on the upper side of the 

strut and measure the maximum value of the 

gap-

- Up to 3 mm: Check the main gear for 

corrosion and cracks (particularly at the 

(0.12 in) curvatures) 

- More than 3 mm (0.12 in) gap: Replace 

the strut. 

25. Replace all of the aircraft attachment 

hardware to the main landing gear. 

26. Install the main landing-gear struts 

(Refer to Chapter 32-10). 

27. Do a test for toe-in and camber. 

(Refer to Chapter 32-10). 

28. Examine the nose-wheel assembly. Look 

especially for correct attachment, cracks and 

deformation. 

29. Remove the nose landing-gear strut 

(Refer to Chapter 32-20). 

30. Visually examine the NLG strut condition. 

Look especially for distortion, corrosion and 

condition of the paint. 

31. Visually examine the NLG strut pivots. 

- Look especially for cracks in the radius of 

the assembly, corrosion and wear. Any 

corrosion needs to be assessed, treated 

and/or the component replaced. 

- Inspect the threads of the lower end of 

the strut for cracks. 

32. Visually examine the NLG strut upper attach 

bolt. Look especially for cracks and 

corrosion. 

33. Do a visual inspection of the NLG bushings 

in the T-panel on the bottom of fuselage. 

- Check for the security of the bushing in 

the T-panel. 

- Do a tap test to check for the condition of 

the surrounding laminate. 

- Check the bond of the T-panel to the 

floor panel and to the fuselage skin, 

Doc#DA201-C1 

Rev. 13 

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Interval (Flight Hours) 

200 1000 6000 Initials. 

® f^ 

05-20-00 Page 17 

30 Apr 2008 
L 

Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

Inspection Items 

Interval (Flight Hours) 

^MU2? 200 1000 6000 Initials. 

34. 

35. 

36. 

37. 

38. 

39. 

40. 

41. 

42. 

43. 

44. 

Examine the nose-gear journal-bearings in 

the bottom of the fuselage. Look especially 

for play. 

Examine the journal in the elastomeric 

spring. Look especially for play. 

Examine the elastomeric spring. Look 

especially for damage and tighten if 

necessary. 

Replace the nose landing gear elastomer 

package (Refer to Chapter 32-20). 

Check the telescopic rod for corrosion and 

excessive wear. 

Visually examine the NLG fork. 

Look especially for cracks and corrosion. 

Install the nose landing-gear strut 

(Refer to Chapter 32-20). 

Examine the nose-wheel fork. Do a test for 

play and caster friction. 

(Refer to Chapter 32-20). 

The friction should be 3 - 5 N (6.75 -

11.25lbs)attheaxle. 

Lubricate the spherical bearing at the top of 

the elastomeric spring. 

(Refer to Chapter 12-20). 

Lower the airplane off jacks. 

(Refer to Chapter 07-10). 

Install the wheel fairings. 

Examine the exterior placards. Make sure 

that they are not damaged and that none are 

missing. 

Replace any that are damaged or missing. 

(Refer to Chapter 11-20). 

0 

Q> 

Q) 

0 

1^ 

Not applicable at 25 hour inspection 

Page 18 

30 Oct 2008 05-20-00 Doc#DA201-C1 

Rev. 14 
DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

C. Cockpit 

All items performed, the findings, as well as their correction must be recorded in accordance with 

an approved procedures manual. Contact Diamond Aircraft if damages are determined which 

cannot be repaired in accordance with an approved procedures manual. 

Inspection Items 

Interval (Flight Hours) 

w 7109 v ^ 200 1000 6000 Initials. 

10. 

Remove the seat shells. 

(Refer to Chapter 25-10). 

Visually examine the seats and seat 

attachments. Look especially for cracks, 

delamination and damage around the 

fastener holes. 

Visually examine the cockpit floor. Look 

especially for cracks or delamination around 

the aft rudder pedal bracket, boarding step, 

and the throttle quadrant opening. 

Examine the safety belts for general 

condition and security of the metal fitting in 

the surrounding composite. 

Make sure the lock mechanism operates 

correctly. 

- Insert the connector into the buckje and 

pull on the connector. Make sure the 

ratchet holds the connector. The 

connector must fall freely from buckle 

when held in a vertical position and when 

you open the cover to the release 

position. 

Examine the cable ties and electrical 

connectors. Pull lightly to make sure they 

are not loose 

Examine the control sticks. Make sure that 

the control stick attachments are not loose 

and do not catch. 

Examine the control stick stops. 

Examine the pitot-static system water traps. 

Examine the stall warning hose. Look 

especially for contamination by water. 

(Refer to Chapter 34-20). 

Examine the flap-actuator indicator and 

position switches. Look especially for 

correct attachment and operation. 

Doc#DA201-C1 

Rev. 13 

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X X 

t; 

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'yy 

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Page 19 

30 Apr 2008 
•<f?W*S' 

Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

11. 

12. 

13. 

14. 

15. 

16. 

17. 

18. 

19. 

20. 

Inspection Items 

Interval (Flight Hours) 

r; 50^ 

Examine the flap-actuator stops and support. 

Look especially for correct attachment. 

Examine for security of the bracket on the 

laminate and cracks in the surrounding 

laminate. 

Examine the locking-device for the wing 

main-bolt. Look especially for: 

- Correct operation. 

- Condition. 

Examine the mounting for the landing gear. 

Look especially for correct attachment and 

lock devices. 

Visually examine the MLG and A-bolt 

attachment brackets. Look especially for: 

- Cracks in, or corrosion of the bracket. 

- Disbond from the laminate. 

- Delamination in the surrounding 

laminate. 

Examine the rudder pedals. Look especially 

for correct attachment and function. 

(Refer to Chapter 27-20) 

Examine the rudder cables and pulleys. 

Look especially for correct attachment and 

function, and for wear, damage and 

corrosion. 

(Refer to Chapter 27-20) 

Examine the areas where the rudder cable 

pulley-brackets attach to the fuselage. Look 

especially for security of the pulley brackets 

on the laminate and cracks in the 

surrounding laminate. 

Examine the brake pipes/hoses and 

components. Look especially for leakage. 

Drain and replace the brake fluid in the 

brake reservoirs. 

(Refer to Chapter 32-40) 

Examine the brake reservoirs on the 

co-pilots side. Make sure the fluid level is 

correct. 

The fluid level must be 12mm to 25mm 

(1/2 to 1 in) below the top face of the 

reservoir filler hole. 

Page 20 

30 Apr 2003 05-20-00 

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0 

© 

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1000 6000 

> 1 

7 ^ 

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Doc#DA201-C1 

Rev. 13 
DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

Inspection Items 

Interval (Flight Hours) 

(5^ 100, 200 1000 6000 Initials. 

^ 

21. Examine the instruments. Make sure that: 

- The markings are clear. 

- The function is correct. 

- Switches are correctly attached. 

22. Examine the interior placards. Make sure 

that they are not damaged and that none 

are missing. 

Replace any that are damaged or missing. 

(Refer to Chapter 11-30). 

23. Remove the instrument panel cover. 

24. Remove the instrument panel. 

(Refer to Chapter 31-10). 

25. Remove the cover box for access to the fuel 

shut-off valve. 

(Refer to Chapter 28-20). 

25. Examine the two fuel hoses that run from the 

drain trap block, along the floor of the cockpit 

to the fuel shut-off valve, as follows: 

NOTE: You must bleed the engine fuel 

system after any work which allows 

air into the airplane fuel supply 

system. Refer to Chapter 73-00 for 

the bleed procedure. 

- Disconnect the fuel hoses from the fuel 

shut-off valve. 

- Disconnect the other ends of the two fuel 

hoses from the maintenance drain-tap 

block. 

- Pull the two fuel hoses out from the fuel 

hose conduit that runs along the floor. 

NOTE: Tie a satisfactory cord to one end 

of each fuel hose so that they pull 

through when each hose is 

removed. This will assist with the 

installation of the hose in the 

conduit. 

Visually inspect the two fuel hoses for 

damage, signs of wear, fuel seepage and 

discoloration. 

Make sure that each hose and the 

connectors are in a fully satisfactory 

condition. Replace a hose that you find 

to be not satisfactory, 

Doc#DA201-C1 

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05-20-00 Page 21 30 Apr 2008 
{ 

Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

Inspection Items 

Interval (Flight Hours) 

5 50> "K;;^ 89 200 1000 6000 Initials. 

27. 

28. 

29. 

30. 

31. 

32. 

33. 

- Put the two fuel hoses back through the 

conduit. Use the cords to help in routing 

the hoses through. Remove and discard 

the cords. 

- Connect the fuel hoses to the 

maintenance drain-tap block. 

- Connect the two fuel hoses to the fuel 

shut-off valve. 

Visually examine the fuel shut-off valve. 

Look especially for signs of corrosion, 

leakage and damage. Make sure that it is 

correctly attached to the firewall. Make sure 

that the fuel hoses are correctly attached. 

Install the cover box that fits over the fuel 

shut-off valve. 

(Refer to Chapter 28-20). 

Visually examine the firewall. Inspect the 

condition of the laminate when viewed from 

the cockpit side for cracks, discoloration and 

delamination. Particularly around the engine 

mount fastener holes and the battery box. 

Examine the structure for security of the 

attaching bolts on the firewall and cracks in 

the surrounding laminate. 

Visually examine the cabin heat valve and 

cabin air ducts. Make sure that they are not 

damaged and are correctly attached. 

Install the instrument panel. 

(Refer to Chapter 31-10). 

Visually examine the cockpit area for any 

signs of fuel leaks. Follow along the fuel 

hose conduit and fuel hoses from the drain 

trap block, along the floor of the cockpit to 

the fuel shut-off valve. Make sure that there 

are no signs of fuel leaks. 

Examine the instrument panel. Make sure 

that: 

- Wiring is correctly attached. 

- Instruments are correctly attached. 

- Hoses are correctly attached. 

- Circuit breakers are correctly attached. 

Page 22 

30 Apr 2008 05-20-00 

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Doc#DA201-C1 

Rev. 13 
rDA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

34. 

35. 

36. 

37. 

38. 

Interval (Flight Hours) 

Inspection Items . 50_y 

Examine the Vacuum inlet filter. (Aircraft 

with pneumatic instrument system only) 

Make sure that: 

- The filter is correctly attached. 

- The filter is clean. 

- Replace the filter at 500 hr intervals. 

Examine the Vacuum system regulator. 

(Aircraft with pneumatic instrument system 

only) 

Make sure that: 

- The regulator is correctly attached. 

<100", 

0 

(y 

- Replace the filter. 

Lubricate the ignition switch: 

- See FAA AD 93-05-06 reference 

ACS/Gerdes service bulletin SB92-01-

ACS, ignition switch 

lubrication/inspection. 

Install the instrument panel cover. 

Examine the compass. Make sure that: 

- The compass is correctly attached. 

- The fluid level is correct. 

9 

200 

X 

X 

X 

X 

1000 

X 

X 

6000 

X 

X 

Initials. 

^ 

1 

••N. 

?^KK^ ^ 

1 

X 

X 

X 

X 

X 

X 

7^-^ 

Not applicable at 25 hour inspection 

Doc#DA201-C1 

Rev. 13 05-20-00 Page 23 

30 Apr 2008 
Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

D. Center Fuselage, Internal 

All items performed, the findings, as well as their correction must be recorded in accordance with 

an approved procedures manual. Contact Diamond Aircraft if damages are determined which 

cannot be repaired in accordance with an approved procedures manual. 

Inspection Items ' ^ 

Interval (Flight Hours) 

200 1000 6000 Initials. 

7. 

8, 

9, 

10. 

Examine the fire extinguisher. Make sure 

the fire extinguisher will release. And make 

sure the fire extinguisher contents are full. 

Do a check of the extinguisher expiry date. 

(Refer to Chapter 26-00). 

Examine the baggage net. Make sure the 

spring clips operate correctly. 

Examine the area where the baggage net 

hooks attach to the fuselage side. Inspect 

the composite for security of the hooks and 

delamination. 

Examine the ELT. (Refer to Chapter 25-60). 

Do a battery check (Refer to Chapter 24-31). 

Look especially for: 

- Charge and capacity. 

- Correct acid level. 

- Correct mounting. 

Examine the battery bay area (aircraft with 

aft mounted battery only). Look especially 

for cleanliness. 

Remove the center fuselage panels on the 

bottom of the airplane for access. 

Remove the baggage compartment floor for 

access. (Refer to Chapter 25-10). 

Remove the battery and battery tray (on 

aircraft with the aft mounted battery only) for 

access. 

(Refer to Chapter 24-31). 

Visually examine the interior of the tail 

section. Look especially for signs of damage 

(dents, scratches, cracks, holes and 

delamination). 

Examine the push rod guides for the elevator 

push-rod. Look especially for correct 

attachment and freedom of movement. 

Page 24 

30 Apr 2008 05-20-00 

X I X 

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Doc#DA201-C1 

Rev. 13 
DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

Interval (Flight Hours) 

Inspection Items 200 1000 6000 Initials. 

'fin 

11. 

12. 

13. 

14. 

15. 

Examine the flap control mechanism on the 

aft control bulkhead. Look especially for 

damage, corrosion, correct attachment and 

lock devices. 

Examine the aileron control system on the 

aft control bulkhead. Look especially for 

wear, damage, corrosion, correct attachment 

and lock devices. 

Do a cable tension test of the rudder control 

cable. (Refer to Chapter 27-20). 

Examine the rudder control lever and cables 

on the B-bulkhead. Look especially for 

damage, corrosion, correct attachment and 

lock devices. 

Examine the rudder control cables in the 

center fuselage. Look especially for wear, 

damage, corrosion and correct lock devices. 

WARNING: DO NOT GET FUEL ON YOU. FUEL CAN CAUSE SKIN DISEASE. 

DO NOT ALLOW FIRE NEAR FUEL. FIRE BURNS AND CAN 

CAUSE INJURY TO PEOPLE AND DAMAGE TO EQUIPMENT. 

16. Defuel the fuel tank. 

(Refer to Chapter 12-10). 

17. Remove the fuel tank. Look for corrosion 

and damage. 

(Refer to Chapter 28-10). 

18. Remove and clean the gascolator filter bowl. 

Install the gascolator filter bowl. 

(Refer to Chapter 28-20). 

19. Examine the fuel tank strap. Look especially 

for rub marks. 

20. Examine the fuel tank and fuel pipes for 

leakage. 

21. Examine the fuel system electrical cables 

and ground strap. Look especially for rub 

marks. 

22. Examine the filler neck of the fuel tank and 

the filler cap. Look especially for fuel leaks 

and damage. 

23. Examine the fuel vent pipe. Look especially 

for rub marks and damage. Make sure the 

vent pipe is clear. 

Doc#DA201-C1 

Rev. 13 

& 

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05-20-00 Page 25 30 Apr 2008 
I 

Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

Inspection Items 

Interval (Flight Hours) 

(50" 100. 200 1000 6000 Initials. 

24. 

25. 

26. 

27. 

28. 

29. 

30. 

Examine the cable ties and electrical 

connectors. Pull lightly to make sure they 

are not loose. 

Visually examine the B-bulkhead. Look for 

cracks and delamination, especially around 

the fuel tank attachments. 

Visually examine the rudder lever mounting 

under the B-bulkhead. Examine for security 

of the bracket on the laminate, elongation of 

holes and cracks in the surrounding 

laminate. 

Examine the roller guides for the rudder 

control cables in the centre fuselage. Look 

especially for damage, play and excessive 

wear. 

Install the battery and battery tray. On 

aircraft with an aft mounted battery only. 

(Refer to Chapter 24-31). 

Install the fuel tank. 

(Refer to Chapter 28-10). 

Do a calibration test of the fuel quantity 

indication system. 

(Refer to Chapter 28-00). 

Install the bottom center fuselage panels. 

Q) 

(V 

'P/ j ' ^ 

/>VJ 

Not applicable at 25 hour inspection 

Page 26 

30 Apr 2008 05-20-00 Doc#DA201-C1 

Rev. 13 
DA20-C1 AMM Diamond. 

c 

Time Limits and 

Maintenance Checks 

E. Rear Fuselage 

All items performed, the findings, as well as their correction must be recorded in accordance with 

an approved procedures manual. Contact Diamond Aircraft if damages are determined which 

cannot be repaired in accordance with an approved procedures manual. 

Inspection Items 

Interval (Flight Hours) 

(3°; 

Examine the complete surface of the rear 

fuselage. Look especially for damage 

(dents, cracks, holes, scratches and 

delamination). 

On aircraft with a rear window, examine 

around the inside and outside of the window. 

Inspect the structure and the seal. Look 

especially for delamination of the structure 

and leaks or breaks in the window seal. 

Visually examine the condition of the paint. 

Look for chips, scratches, UV damage. 

Do a visual inspection and a tap test of the 

fuselage skin. 

- Inspect for disbonding between internal 

composite components and skin. 

Examine the push rod guides for the elevator 

push-rod. Look especially for correct 

attachment. And freedom of movement. 

Examine the rudder-control cables and 

turnbuckles. Look especially for wear, 

damage, corrosion and correct lock devices. 

X ^ , 

U 

200 1000 6000 

& 

& 

Initials. 

r\ 

i^ 

^ 

^ 

Not applicable at 25 hour inspection 

Doc#DA201-C1 

Rev. 13 05-20-00 Page 27 

30 Apr 2008 
Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

F. Tail 

All items performed, the findings, as well as their correction must be recorded in accordance with 

an approved procedures manual. Contact Diamond Aircraft if damages are determined which 

cannot be repaired in accordance with an approved procedures manual. 

Inspection Items 

Interval (Flight Hours) 

( ^ 200 1000 6000 Initials. 

6. 

7, 

Examine the complete surface of the aft part 

of the fuselage, vertical stabilizer, and 

horizontal stabilizer. Look especially for 

damage (dents, cracks, holes, scratches and 

delamination). Look especially around the 

access panels. 

Do a visual inspection and a tap test of the 

vertical stabilizer and horizontal stabilizer. 

- Inspect for disbonding between internal 

composite components and the skin. 

- Inspect for disbonding between the 

trailing edge and the skin. 

Do a visual inspection and atap-fest of the 

leading edge of the horizontal stabilizer. 

Examine for disbonds and cracks above or 

below the overtap seam. 

Visually examine the forward mounting 

bracket of the horizontal stabilizer. Look 

especially for: 

- Cracks in the bond to the plate. 

- Delamination in the rib around the 

'. fasteners. 

- The condition of the spherical bearing. 

- The fit of the pin in the bearing. 

Visually examine the drain holes in the 

horizontal stabilizer. Make sure that they are 

open. 

Visually examine the condition of the paint. 

Look for chips, scratches, UV damage. 

Examine the lower fin. Look especially for 

damage to the bottom of the fin and correct 

attachment. 

Do a visual inspection and a tap test. 

Inspect the fuselage skin around the lower 

tail fin for cracks. Inspect bond line to vertical 

stabilizer web for cracks. 

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Time Limits and 

Maintenance Checks 

10. 

Inspection Items 

Interval (Flight Hours) 

50 

11. 

12. 

13. 

14. 

15. 

16. 

17, 

18, 

19. 

20, 

Remove the rudder. 

- Visually examine the hinge pin for cracks, 

corrosion and fit in the composite. 

- On aircraft that have a sleeve installed 

over the hinge pin, replace the sleeve if it 

is damaged or worn. 

- Lubricate the hinge bushes. 

(Refer to Chapter 55-40). 

Do a visual inspection and a tap test of the 

rudder. 

- Examine the skin for delamination, 

cracks, dents and scratches. 

- Examine the paint for chips, scratches 

and UV damage. 

- Examine for damage to the core. 

- Examine for a disbond between the skin 

and the core. 

Visually examine the drain holes in the 

rudder. Make sure that they are open. 

View through the access holes in the vertical 

stabilizer spar and visually inspect internal 

composite components for disbonding with 

skin, and for delamination and cracks. 

Examine the rudder mounting and control 

cable connections. 

Examine the rudder support bracket. 

Visually examine the rudder pivot bearing for 

corrosion and wear. 

Examine the bottom edge of the rudder. 

Look especially for cracks and deformation. 

Examine the rudder-stop reinforcement bars. 

Look especially for cracks and corrosion. 

Examine the trim actuator. Look especially 

for correct attachment and wear. 

Examine the fork assembly on the trim 

actuator. Look especially for cracks and 

corrosion. 

Remove the horizontal stabilizer. Examine 

the horizontal stabilizer for damage. 

(Refer to Chapter 55-10). 

Doc#DA201-C1 

Rev. 13 

200 1000 6000 Initials. 

05-20-00 

"?. 

Page 29 

30 Apr 2008 
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Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

21. 

22. 

23. 

24. 

25. 

26. 

27. 

28, 

29, 

Interval (Flight Hours) 

Inspection Items 

Visually examine the bushings at the aft 

horizontal stabilizer attachment. Examine 

for corrosion, cracks, delamination or cracks 

in composite around bushing. 

Remove the elevator from the horizontal 

stabilizer (Refer to Chapter 55-20). 

Examine the elevator for damage. Look 

especially for correct attachment and lock 

devices. 

(Refer to Chapter 27-30). 

Do a visual inspection and a tap test of the 

elevator. 

- Examine the skin for delamination, 

cracks, dents and scratches. 

- Examine the paint for chips, scratches 

and UV damage. 

- Examine for damage to the core. 

- Examine for a disbond between the skin 

and the core. 

Visually examine the drain holes in the 

elevator. Make sure that they are open. 

Do a visual inspection of the elevator hinges. 

Look especially for cracks, corrosion and the 

fit of the clevis pin in the hinge. 

Remove and replace the elevator hinge 

hardware. 

Examine the elevator hinges and control 

horn. Check the laminate around the hinges 

and the control horn fasteners for cracks, 

corrosion or delamination. 

Look especially for too much play. 

Play allowed: 

- Axial: ± 1,00 mm (± 0.04 in). 

- Radial: ± 0,25 mm (± 0.01 in). 

Visually examine the bronze bushings in the 

elevator. Examine for corrosion, cracks, and 

correct tolerance. 

50 J 100 

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DA20-C1 AMM ^^Diautond . 

30. 

31. 

32. 

33. 

34. 

35. 

Time Limits and 

Maintenance Checks 

Interval (Flight Hours) 

Inspection Items (5 0 j _100^ 

Remove the elevator horizontal push-rod 

and examine it for damage. Look especially 

for rub marks and excessive wear. 

The maximum wear permitted is 0.381 mm 

(0.015 in). 

Measure the amount of wear as follows: 

- Take a measurement of the push-rod 

diameter at the edge of the paint 

- Take a measurement of the push-rod 

diameter at the middle of the wear mark 

- Compare the two measurements. If the 

maximum wear permitted is exceeded, 

replace the push-rod. 

Install the pushrod. 

(Refer to Chapter 27-30). 

Install the elevator back on the horizontal 

stabilizer (Refer to Chapter 55-20). 

Examine the forward mounting brackets for 

the horizontal stabilizer. 

Replace all of the mounting hardware. 

(Refer to Chapter 12-20). 

On the horizontal stabilizer: 

Replace the four bolts which attach the 

horizontal stabilizer mount plate to the 

vertical stabilizer. 

Install the horizontal stabilizer. 

(Referto Chapter 55-10). 

Install the rudder, 

(Refer to Chapter 55-40). 

200 

X 

1000 

X 

X 

X 

X 

6000 

X 

X 

X 

X 

X 

X 

Initials. 

_: 

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Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

G. Wings 

All items performed, the findings, as well as their correction must be recorded in accordance with 

an approved procedures manual. Contact Diamond Aircraft if damages are determined which 

cannot be repaired in accordance with an approved procedures manual. 

Inspection Items 

Interval (Flight Hours) 

r 50 > -foT"* 200 1000 6000 Initials. 

3. 

Examine the complete surface of the wings. 

Look especially for damage (dents, cracks, 

holes and delamination). 

Examine the paint coat. 

Do a visual inspection and a tap test of the 

upper and lower wing skins. Examine for 

damage to the core or a disbond between 

the skin and core. 

Do a visual inspection and a tap test of the 

leading edge. Examine for disbonds and 

cracks above or below the overlap seam. 

Do a visual inspection and a tap test to 

examine the main spar bonding with the 

wing skins. 

Remove the wings (Refer to Chapter 57-10). 

- Examine the A bolts and bushings for 

security in surrounding composite, 

tightness of fit of pin/bolt, cracks, 

corrosion, wear and distortion. 

- Replace the A bolts if there is more than 

0.1 mm (0.004 in) of radial play. 

- Grease the A bolts. 

- Examine the B-bolts and bushings for 

security in surrounding composite, 

tightness of fit of pin/bolt, cracks, 

corrosion, wear and distortion. 

- Replace the B bolts if there is more than 

0,1 mm (0,004 in) of radial play, 

- Grease the B-bolts. 

(Refer to Chapter 12-20). 

Do a visual inspection and a tap test of the 

wing roots (in front and behind the spar) to 

examine the bonding with the skins. 

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Time Limits and 

Maintenance Checks 

Inspection Items Initials. 

10. 

11. 

12. 

13. 

14. 

At the lower wing, remove the tie-down ring 

to check for damage to the hole. Check for 

delamination, cracks and elongation of the 

hole. 

Visually examine the internal ribs through 

the lower wing inspection panels. 

- Check for the condition of the laminate 

on the ribs. 

- Check for cracks and delamination 

around the bellcrank brackets and a 

disbond between the bracket and rib. 

- Check the condition of the bellcrank 

brackets. Look especially for cracks, 

elongation of the bellcrank mounting 

holes, corrosion and chipped paint. 

Do a visual inspection and a tap test of the 

trailing edge spar. 

- Examine for the condition of the laminate 

and bond of the trailing edge to the skin. 

- Examine for the bonding of the flap and 

aileron hinges to the trailing edge and 

skin. 

- Examine the bonding of the flap up-stop 

rib to the trailing edge and skin. 

Visually examine the main spar flange joint 

and web, outboard from the root rib. Look 

through the root rib openings. Look for signs 

of damage (delamination). 

Visually examine the main spar web 

sandwich structure, outboard from the root 

rib. Look through the root rib openings. 

Look for condition of laminate, delamination, 

condition of core. 

Visually examine the wing roots (in front and 

behind the spar) to inspect the joints with the 

main spar and spar stump. Examine the 

condition of the laminate. Look especially 

for damage (cracks and delamination). 

Visually examine the main bolt bushing in 

the spar web. Look especially for corrosion 

or wear of bushing, bond of bushing in spar 

stump. Make sure of a tight fit of the main 

pin within the bushing. 

Remove the ailerons from the wings. 

(Refer to Chapter 57-60), 

Doc#DA201-C1 

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Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

15. 

16. 

17. 

18. 

19. 

20. 

21. 

22. 

23, 

Inspection Items 

Visually examine the ailerons. Look 

especially for damage (dents, cracks, holes 

and delamination). 

Do a visual inspection and tap test of the 

ailerons. 

- Examine the paint for chips, scratches 

and UV damage. 

- Inspect the skin for delamination. 

- Inspect for damage to the core or 

disbond between the skin and the core. 

- Inspect the ribs for bonding with the 

skins. 

Remove and replace the aileron hinge 

hardware. 

Examine the aileron hinges and control 

horns. Check the laminate around the 

hinges and the control horn fasteners for 

cracks, corrosion or delamination. 

Look especially for too much play. 

Play allowed: 

- axial; ± 1.00 mm (± 0.04 in). 

- radial: ± 0.25 mm (± 0.01 in). 

Visually examine the drain holes in the 

ailerons. Make sure that they are open. 

Install the ailerons back on the wings.' 

(Refer to Chapter 57-60). 

Visually examine the mass balance 

attachment through the access hole on the 

lower surface. Inspect for cracks in the 

laminate and bonding paste around the 

fasteners. 

Remove the flaps from the wings. 

(Refer to Chapter 57-50). 

Examine the flaps. Look especially for 

damage (dents, cracks, holes and 

delamination). 

Interval (Flight Hours) 

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200 

X 

1000 

X 

6000 

X 

Initials. 

(S) 

0 

fc 

'p^ 

7^ 

Doc#DA201-C1 

Rev. 13 
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DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

Inspection Items 

Interval (Flight Hours) 

y " "loj 200 1000 6000 Initials. 

24. 

25. 

26. 

27. 

28, 

Do a visual inspection and tap test of the 

flaps. 

- Examine the paint for chips, scratches 

and UV damage. 

- Inspect the skin for delamination. 

- Inspect for damage to the core or 

disbond between the skin and the core. 

- Inspect the ribs for bonding with the 

skins. 

Remove the flap push-rods and examine 

them for damage. Look especially for rub 

marks and excessive wear. The maximum 

wear permitted is 0.127 mm (0.005 in). 

Measure the amount of wear as follows: 

- Take a measurement of the push-rod 

diameter at the edge of the paint 

- Take a measurement of the push-rod 

diameter at the middle of the wear mark 

- Compare the two measurements. If the 

maximum wear permitted is exceeded, 

replace the push-rod. 

Install the pushrods. 

Remove and replace the flap hinge 

hardware. 

Examine the flap hinges and control horn. 

Check the laminate around the hinges and 

the control horn fasteners for cracks or 

delamination. 

Look especially for too much play. 

Play allowed: 

- Axial: + 1,00 mm (+ 0,04 in) 

- Radial: ± 0,25 mm (± 0,01 in). 

Install the flaps back on the wings, 

(Refer to Chapter 57-50). 

G - ^ 

Doc#DA201-C1 

Rev. 14 05-20-00 Page 35 

30 Oct 2008 
Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

Inspection Items 

Interval (Flight Hours) 

5 IHQ-- 200 1000 6000 Initials. 

29. 

30. 

31. 

32. 

33. 

34. 

Remove the flap and aileron bellcrank 

access panels in the wing (Refer to Chapter 

52-40). 

- Examine the aileron and flap control 

system. Look especially for correct 

attachment and lock devices 

(Refer to Chapter 27-10 and 27-50). 

- Install the access panels. 

Examine the pitot head. Look especially for 

correct attachment. 

Examine the vent and drain holes in the 

wings, fuselage and control surfaces. 

Make sure that they are clear. 

Do a test for axial play in the B-bolts. 

(Refer to Chapter 57-10). 

Do a visual inspection and a tap test of the 

spar bridge. 

- Examine the condition of the laminates 

and the bond to the fuselage. 

Look especially around: 

- The LH and RH A-bolt bushing. 

- The B-bolt bushing. 

- The MLG brackets. 

- The LH and RH top aft outer corners 

(behind the back-rest). 

Do a visual inspection of the inside spar 

bridge. 

Do a visual inspection and a tap test. 

Check for delamination of fuselage skin 

outboard of the seat fastener through the 

side of spar bridge. 

Page 35 

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Rev. 14 
DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

Inspection Items 

Interval (Flight Hours 

200 1000 6000 Initials. 

35. 

36. 

37. 

38. 

Remove the aileron push-rods and examine 

them for damage. Look especially for rub 

marks and excessive wear. The maximum 

wear permitted is 0.254 mm (0.010 in). 

Measure the amount of wear as follows: 

- Take a measurement of the push-rod 

diameter at the edge of the paint 

- Take a measurement of the push-rod 

diameter at the middle of the wear mark 

- Compare the two measurements. If the 

maximum wear permitted is exceeded, 

replace the push-rod. 

Install the aileron push-rods. 

(Refer to Chapter 27-10). 

Visually examine the main pin bushing in the 

spar stump. 

Replace the main pin bushing if it is 

damaged. 

Visually examine the main pin bushing in the 

spar bridge. 

Replace the main pin bushing if it is 

damaged. 

Install the wings. 

(Refer to Chapter 57-10). 

Doc#DA201-C1 

Rev. 14 05-20-00 Page 37 

30 Oct 2008 
'f"^^^ 

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IP' 

Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

H. General 

All items performed, the findings, as well as their correction must be recorded in accordance with 

an approved procedures manual. Contact Diamond Aircraft if damages are determined which 

cannot be repaired in accordance with an approved procedures manual. 

Inspection Items 

Interval (Flight Hours) 

100^ 200 1000 6000 Initials. 

2. 

Examine the pitot-static system. Look 

especially for leaks. 

- Do a low-range static leak test 

(Refer to Chapter 34-10). 

- Do a pitot test 

(Refer to Chapter 34-10). 

- Make sure the pitot-static system is 

clean. 

Perform a functional check of the pitot static 

heat system (if installed). 

Inspection Interval; 

1000 hrs. or 12 months, whichever 

comes first. 

Refer to chapter 34-10 

Lubricate the airplane. 

- Refer to chapter 12-20 

Measure the play in the aileron and elevator 

controls with the control surfaces locked 

(Refer to Chapter 27-30). Look especially 

for too much play. Do the test at the top of 

the control stick. 

Maximum play allowed: 

- 10 mm (0.375 in) 

- Refer to Chapter 27-10. 

Do a function test of the aileron control 

system. 

- Refer to Chapter 27-10, 

Do a function test of the rudder control 

system. 

- Refer to Chapter 27-20, 

Do a function test of the elevator control 

system. 

- Refer to Chapter 27-30. 

Page 38 

30 Oct 2008 05-20-00 

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Doc#DA201-C1 

Rev. 14 
V 

DA20-C1 AMM Diamond. 

Time Limits and 

Maintenance Checks 

Inspection Items 

Interval (Flight Hours) 

doj ^P5' 

^ 

200 1000 6000 initials. 

7 ^ 8. 

10. 

11. 

Do an actuator-motor test of the trim-system. 

Look especially for correct operation and 

indication. 

- Refer to Chapter 27-31. 

Do a function test of the flap system (Refer 

to Chapter 27-50). Look especially at the 

pre-load. With the flaps set to CRUISE in 

the up position. 

- Correct pre-load: 

30 - 50 N (6.7-11.2 lbs) 

Do an operational test of the external lights. 

Examine the airplane. Look especially for 

loose items and tools. Close all access 

panels. Install these items: 

- Engine cowlings. 

- The instrument panel cover. 

- The seat shells. 

- The control-stick boots. 

< l 

WARNING: DO NOT LET PERSONS INTO THE DANGER AREA OF THE 

PROPELLER. PROPELLERS CAN CAUSE INJURY OR DEATH. 

WARNING: SET THE PARKING BRAKE TO ON. IF YOU DO NOT DO THIS THE 

AIRPLANE CAN MOVE. THIS CAN CAUSE INJURY OR DEATH. 

S 

f 

12. 

13. 

14. 

15, 

16. 

17. 

Set the parking brake to ON. 

Put the chocks against the main airplane 

wheels. 

Do the post maintenance operational test. 

- For the engine run procedures refer to 

the DA20-C1 Flight Manual, 

- For the operational test refer to TCM 

Maintenance Manual Chapter 23, 

- Record the data (Refer to Paragraph 7). 

Examine the engine for leakage. 

Make sure the engine oil filter is tight, 

- Refer to Chapter 79-00, 

Do a test flight. Record the engine ground 

test and the flight test reports in the Airplane 

Maintenance Log. 

o 

(2- 7 ^ 

Doc#DA201-C1 

Rev. 14 05-20-00 Page 39 30 Oct 2008 
••• ( 

Time Limits and 

Maintenance Checks Diamond. DA20-C1 AMM 

5. Maintenance Report 

Complete a copy of the Maintenance Report after all of the applicable maintenance tasks in the 

Maintenance Checklist have been initialed. 

DA20-C1 

Airplane Serial Number: 

Check: 

REMARKS: 

1 

/6DA£_ 

noy^i 

(50 hr. 

Registration Number: 

.^ooV. 

A./ :^^C, ^ 

200 hr., 1000 hr., 6000 hr.. Annual) | 

The airplane is airworthy with respect to its maintenance condition. 

Place: 

Date: 

Authorized: 17 

Page 40 

30 Oct 2008 05-20-00 Doc#DA201-C1 

Rev. 14 
EXHIBIT 2 
•••• ^ 

^•• ^ 

DAT E 

Ft 

DAILV 

TOTA L 

HRS. MIN . 

OTA L AIR 

TIME SINCE 

MFG. 

HRS. MIN. 

NOTE: 

ENGINEERING RCCORD 

USE BOTH PAOEl AND AIMANY LINK! Al REQUIRED rOR COMPLET 

m*Mm9tT MCJ»^»W¥9 V 

N383CA Airframe log for 100 inspections 

Date: 4/19/2009 

Tach time: 932.1 

Airframe total time: 932.1 

Engine total lime since new: 932.1 

Propeller total time since new: 249.9 

Lubricated Aircraft serx'iced tires and battery check ops of ELT is ok check. ELT battery 

due date SEPT /2010 all A.D's checked through 2009-7. 1 certify that this aircraft was 

inspected l.A.W. FAR 43APP/D 100 HOUR INSPETION and determent it to be in 

air^^'orlhy condition END. PAUL MASARACpilArA&P 104569374 

^ammmw ^cmm^t^w 

AIRFRAME log 50 inspection 

Engine time since new: 982.2 

N383CA 

DATE: 05/31/2009 

Tach time: 982.2 

Aircraft total time: 982.2 

Lubed aircraft, checked tires and brake fluid. serA'iced battery JAW 50 HOUR 

N^IMI^SIM'^PT? ! ^iV'p?.'^'5^?]^B^inirwonh;ct^tio n e"^^^ NAME SAMER ELSAYED .:^^--:Crr:::-: . A&P 3245675 

V ^ -te 

V r 

vAf % 

N383CA AIRFRAME LOG 

DATE: 05/31/2009 

Tach time: 982.2 

.Aircraft total time: 1396.8 

Inspected NLG and found damaged on assy. Removed and replaced assy. With new VFH 

20-3220-08-00 S/N CS0700186-10000. Removed and replaced with new the shock 

absorbers P/N 20-3220-05-03. All work done lAA/W Diamond DA-20 M/M AND IS 

DETERMEND TO BE in airworthy condition end^^^ ^ 

NAME P.AUL MASARACCHIA Qj)/^;^^^,J^...- ^ .A&P 104569374 

CARRfED FORWARD 
CERTIFICATE OF SERVICE 

I hereby certify that I have this date served by regular U.S. mail, postage prepaid, an original and 

one (1) copy of the foregoing Motion for Partial Summary Judgment addressed to: 

Attention: Hearing Docket Clerk, AGC-430 

Wilbur Wright Building 

Federal Aviation Administration 

800 Independence Avenue, S.W. 

Room 2014 

Washington, D.C. 20591 

I hereby certify that I have this date sent via facsimile and first class mail a copy of the foregoing 

Motion for Partial Summary Judgment addressed to: 

The Honorable Ronnie A. Yoder 

Chief Administrative Law Judge 

Office of Hearings, M-20 

U. S. Department of Transportation 

1200 New Jersey Ave., S.E. 

East Building Ground Floor, Room E12-320 

Washington, DC 20590 

Tel: 202 366-3212 

Fax: 202 366-7536 

Zachary M. Berman, Esq. 

FAA Eastern Region, AEA-7 

1 Aviation Plaza, Room 561 

Jamaica, NY 11434 

Tel: 718 553-3258 

Fax:718 533-5699 

Dated this 31th day of May 2011. 

Respectfully s; 

GREBQRY/S^VINTON, ESQ. 

The Ayiaticoj^aw Firm 

One Research Court, Suite 450 

Rockville,MD 20850 

Counsel for Respondent