This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

37955 

Vol. 74, No. 145 

Thursday, July 30, 2009 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2008–0052; Directorate 

Identifier 2008–NE–01–AD] 

RIN 2120–AA64 

Airworthiness Directives; Engine 

Components, Inc. (ECi) Reciprocating 

Engine Cylinder Assemblies 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for Lycoming Engines 

(formerly Textron Lycoming) models 

320, 360, and 540 series, ‘‘Parallel 

Valve’’ reciprocating engines, with 

certain Engine Components, Inc. (ECi) 

cylinder assemblies, part number (P/N) 

AEL65102 series ‘‘Titan,’’ installed. 

That AD currently requires initial and 

repetitive visual inspections and 

compression tests to detect cracks at the 

head-to-barrel interface, replacement of 

cylinder assemblies found cracked, and 

replacement of certain cylinder 

assemblies at new, reduced times-inservice. This proposed AD would 

require the same actions, but for an 

expanded population of cylinder 

assemblies. This proposed AD results 

from reports of 10 additional cylinder 

head separations since issuing AD 

2008–19–05, on cylinder serial numbers 

not listed in that AD. We are proposing 

this AD to prevent loss of engine power 

due to cracks at the head-to-barrel 

interface and possible engine failure 

caused by separation of a cylinder head, 

which could result in loss of control of 

the aircraft. 

DATES: We must receive any comments 

on this proposed AD by September 28, 

2009. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

AD: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

FOR FURTHER INFORMATION CONTACT: 

Peter W. Hakala, Aerospace Engineer, 

Special Certification Office, FAA, 

Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, TX 76193; e-mail: 

peter.w.hakala@faa.gov; telephone (817) 

222–5145; fax (817) 222–5785. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA– 

2008–0052; Directorate Identifier 2008– 

NE–01–AD’’ in the subject line of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this proposed AD. 

Using the search function of the Web 

site, anyone can find and read the 

comments in any of our dockets, 

including, if provided, the name of the 

individual who sent the comment (or 

signed the comment on behalf of an 

association, business, labor union, etc.). 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78). 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is the 

same as the Mail address provided in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

Discussion 

The FAA proposes to amend 14 CFR 

part 39 by superseding AD 2008–19–05, 

Amendment 39–15672 (73 FR 53105, 

September 15, 2008). That AD requires 

initial and repetitive visual inspections 

and compression tests to detect cracks at 

the head-to-barrel interface, replacement 

of cylinder assemblies found cracked, 

and replacement of certain cylinder 

assemblies, at new reduced times-inservice. That AD was the result of 

reports of 45 failures with head 

separations of ECi cylinder assemblies. 

That condition, if not corrected, could 

result in loss of engine power due to 

cracks at the head-to-barrel interface in 

the cylinder assemblies and possible 

engine failure caused by separation of a 

cylinder head, which could result in 

loss of control of the aircraft. 

Actions Since AD 2008–19–05 Was 

Issued 

Since AD 2008–19–05 was issued, we 

received reports of 10 additional 

cylinder head separations, on cylinder 

serial numbers not listed in that AD. To 

date, there have been a total of 55 head 

separations resulting in engine 

shutdowns and emergency landings in 

airplanes and helicopters. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 

condition that is likely to exist or 

develop on other products of this same 

type design. For that reason, we are 

proposing this AD, which would require 

initial and repetitive visual inspections 

and compression tests to detect cracks at 

the head-to-barrel interface, replacement 

of cylinder assemblies found cracked, 

and replacement of certain cylinder 

assemblies, at new reduced times-inservice. The proposed AD would 

require: 


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• Determining if Group ‘‘A’’ or Group 

‘‘B’’ ECi cylinder assemblies, P/N 

AEL65102 series ‘‘Titan,’’ with cylinder 

head P/N AEL85099, are installed on 

your engine. 

• For any Group ‘‘A’’ cylinder 

assembly, performing initial and 

repetitive visual inspections and 

compression tests, and replacement not 

later than 2,000 operating hours time-inservice (TIS) or within 25 operating 

hours TIS if the cylinder assembly 

exceeds 2,000 operating hours TIS on 

the effective date of the proposed AD. 

• For any Group ‘‘A’’ cylinder 

assembly installed in a helicopter, 

performing the same initial and 

repetitive visual inspections and 

compression tests, but replacement not 

later than 1,500 operating hours TIS or 

within 25 operating hours TIS if the 

cylinder assembly exceeds 1,500 

operating hours TIS on the effective date 

of the proposed AD. 

• Expanding the serial numbers 

affected of Group ‘‘B’’ cylinder 

assemblies, and performing the same 

initial visual inspection and 

compression test, and replacement not 

later than 350 operating hours TIS or 

within 25 operating hours TIS if the 

cylinder assembly exceeds 350 

operating hours TIS on the effective date 

of the proposed AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 18,000 ECi cylinder 

assemblies installed in aircraft of U.S. 

registry. The visual inspection and 

compression tests would take about 4 

work-hours for each engine. An 

individual cylinder replacement would 

require $1,100 for parts and 6 workhours. Lycoming engines with a set of 

4 ECi cylinders would require 12 workhours for the cylinder replacement. 

Lycoming engines with a set of 6 ECi 

cylinders would require 16 work-hours 

for the cylinder replacement. We 

estimate 18 percent of the affected 

population of cylinders would be 

replaced. We estimate the total cost of 

the AD to U.S. operators to be 

$10,172,000. Our estimate is exclusive 

of any possible warranty coverage. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); and 

3. Would not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD. See the ADDRESSES

section for a location to examine the 

regulatory evaluation. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed Amendment 

Under the authority delegated to me 

by the Administrator, the Federal 

Aviation Administration proposes to 

amend 14 CFR part 39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by 

removing Amendment 39–15672 (73 FR 

53105, September 15, 2008) and by 

adding a new airworthiness directive to 

read as follows: 

Engine Components, Inc. (ECi): Docket No. 

FAA–2008–0052; Directorate Identifier 

2008–NE–01–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

September 28, 2009. 

Affected ADs 

(b) This AD supersedes AD 2008–19–05, 

Amendment 39–15672. 

Applicability 

(c) If your engine has not been overhauled, 

or not had any cylinder assemblies replaced 

since new, no further action is required. 

(d) This AD applies to the Lycoming 

Engines (formerly Textron Lycoming) models 

320, 360, and 540 series, ‘‘Parallel Valve,’’ 

reciprocating engines listed in Table 1 of this 

AD, with ECi cylinder assembly, part number 

(P/N) AEL65102 series ‘‘Titan,’’ and with 

cylinder head, P/N AEL85099, installed. 

(1) The applicable cylinder assembly serial 

numbers (SNs) are SN 1138–02 through SN 

35171–22, (referred to in this AD as Group 

‘‘A’’ cylinder assemblies); and 

(2) SN 35239–01 through SN 42179–30 

(referred to in this AD as Group ‘‘B’’ cylinder 

assemblies). 

(3) The cylinder assembly P/N is at the 

crankcase end of the cylinder assembly, and 

might be difficult to see. As a guide in 

determining if your cylinder assemblies are 

affected, all affected cylinder assemblies have 

cylinder head P/N AEL85099. The cylinder 

head P/N is at the top of the cylinder head, 

near the intake and exhaust valve springs, 

and is easier to locate than the cylinder 

assembly P/N. 

(4) The set of numbers appearing on the 

cylinder, above and to the left of the SN, in 

the form of ‘‘123456’’ is not used for 

determining applicability. 

TABLE 1—ENGINE MODELS

Cylinder assembly part number Installed on engine models 

AEL65102–NST04 .......................... O–320–A1B, A2B, A2C, A2D, A3A, A3B, B2B, B2C, B2D, B2E, B3B, B3C, C2B, C2C, C3B, C3C, D1A, 

D1AD, D1B, D1C, D1D, D1F, D2A, D2B, D2C, D2F, D2G, D2H, D2J, D3G, E1A, E1B, E1C, E1F, E1J, 

E2A, E2B, E2C, E2D, E2E, E2F, E2G, E2H, E3D, E3H. 

IO–320–A1A, A2A, B1A, B1B, B1C, B1D, B1E, B2A, D1A, D1AD, D1B, D1C, E1A, E1B, E2A, E2B. 

AEIO–320–D1B, D2B, E1A, E1B, E2A, E2B. 


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TABLE 1—ENGINE MODELS—Continued 

Cylinder assembly part number Installed on engine models 

AIO–320–A1A, A1B, A2A, A2B, B1B, C1B. 

LIO–320–B1A. 

AEL65102–NST05 .......................... IO–320–C1A, C1B, C1F, F1A. 

LIO–320–C1A. 

AEL65102–NST06 .......................... O–320–A1A, A2A, A2B, A2C, A3A, A3B, A3C, E1A, E1B, E2A, E2C, (also, an O–320 model with no suffix). 

IO–320–A1A, A2A. 

AEL65102–NST07 .......................... IO–320–B1A, B1B. 

LIO–320–B1A. 

AEL65102–NST08 .......................... O–320–B1A, B1B, B2A, B2B, B3A, B3B, B3C, C1A, C1B, C2A, C2B, C3A, C3B, C3C, D1A, D1B, D2A, 

D2B, D2C. 

AEL65102–NST10 .......................... O–360–A1A, A1C, A1D, A2A, A2E, A3A, A3D, A4A, B1A, B1B, B2A, B2B, C1A, C1C, C1G, C2A, C2B, 

C2C, C2D, D1A, D2A, D2B. 

IO–360–B1A, B1B, B1C. 

HO–360–A1A, B1A, B1B. 

HIO–360–B1A, B1B. 

AEIO–360–B1B. 

O–540–A1A, A1A5, A1B5, A1C5, A1D, A1D5, A2B, A3D5, A4A5, A4B5, A4C5, A4D5, B1A5, B1B5, B1D5, 

B2A5, B2B5, B2C5, B4A5, B4B5, D1A5, E1A, E4A5, E4B5, E4C5, F1A5, F1B5, G1A5, G2A5. 

IO–540–C1B5, C1C5, C2C, C4B5, C4B5D, C4C5, D4A5, D4B5, N1A5. 

AEL65102–NST12 .......................... O–360–A1A, A1AD, A1D, A1F, A1F6, A1F6D, A1G, A1G6, A1G6D, A1H, A1H6, A1J, A1LD, A1P, A2A, 

A2D, A2F, A2G, A2H, A3A, A3AD, A3D, A4A, A4AD, A4D, A4G, A4J, A4JD, A4K, A4M, A4N, A4P, 

A5AD, B1A, B2C, C1A, C1C, C1E, C1F, C1G, C2A, C2B, C2C, C2D, C2E, C4F, C4P, D2A, F1A6, 

G1A6. 

HO–360–C1A. 

LO–360–A1G6D, A1H6. 

HIO–360–B1A, B1B, G1A. 

LTO–360–A1A6D. 

TO–360–A1A6D. 

IO–360–B1B, B1BD, B1D, B1E, B1F, B1F6, B1G6, B2E, B2F, B2F6, B4A, E1A, L2A, M1A, M1B. 

AEIO–360–B1B, B1D, B1E, B1F, B1F6, B1G6, B1H, B2F, B2F6, B4A, H1A, H1B. 

O–540–A4D5, B2B5, B2C5, B2C5D, B4B5, B4B5D, E4A5, E4B5, E4C5, G1A5, G2A5, H1A5, H1A5D, 

H1B5, H1B5D, H2A5, H2A5D, H2B5D. 

IO–540–C4B5, C4B5D, C4D5, C4D5D, D4A5, D4B5, D4C5, N1A5, N1A5D, T4A5D, T4B5, T4B5D, T4C5D, 

V4A5, V4A5D. 

AEIO–540–D4A5, D4B5, D4C5, D4D5. 

AEL65102–NST26 .......................... IO–540–J4A5, R1A5. 

TIO–540–C1A, E1A, G1A, H1A. 

AEL65102–NST38 .......................... IO–360–F1A. 

TIO–540–AA1AD, AB1AD, AB1BD, AF1A, AG1A, AK1A, C1A, C1AD, K1AD. 

LTIO–540–K1AD. 

AEL65102–NST43 .......................... O–360–J2A. 

O–540–F1B5, J1A5D, J1B5D, J1C5D, J1D5D, J2A5D, J2B5D, J2C5D, J2D5D, J3A5, J3A5D, J3C5D. 

IO–540–AB1A5, W1A5, W1A5D, W3A5D. 

AEL65102–NST44 .......................... O–540–L3C5D. 

The Lycoming Engines (formerly Textron 

Lycoming) models 320, 360, and 540 series, 

‘‘Parallel Valve’’, reciprocating engines are 

installed on, but not limited to, the aircraft 

listed in the following Table 2: 

TABLE 2—ENGINES INSTALLED ON, BUT NOT LIMITED TO

Engine models Installed on, but not limited to 

O–320–A1A .................................... Piper Aircraft: Tri-Pacer (PA–22 ‘‘150’’, PA–22S ‘‘150’’), Apache (PA–23), Pawnee (PA–25). 

Doyn Aircraft: Doyn-Cessna (170, 170A, 170B). 

Mooney Aircraft: Mark (20A). 

Dinfia: Ranquel (1A–46). 

Simmering-Graz Pauker: Flamingo (SGP–M–222). 

Aviamilano: Scricciolo (P–19). 

Vos Helicopter Co.: Spring Bok. 

O–320–A1B .................................... Piper Aircraft: Tri-Pacer (PA–22 ‘‘150’’, PA–22S ‘‘150’’), Apache (PA–23). 

Doyn Aircraft: Doyn-Cessna (170, 170A, 170B). 

S.O.C.A.T.A.: Horizon (Gardan). 

O–320–A2A .................................... Piper Aircraft: Tri-Pacer (PA–22 ‘‘150’’, PA–22S ‘‘150’’), Agriculture (PA–18A ‘‘150’’), Super Cub (PA–18 

‘‘150’’), Caribbean (PA–22 ‘‘150’’), Pawnee (PA–25). 

Intermountain Mfg. Co.: Call Air Texas (A–5, A–5T). 

Lake Aircraft: Colonial (C–1). 

Rawdon Bros.: Rawdon (T–1, T–15, T–15D). 

Shinn Engineering: Shinn (2150–A). 


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TABLE 2—ENGINES INSTALLED ON, BUT NOT LIMITED TO—Continued 

Engine models Installed on, but not limited to 

Dinfia: Ranquel (1A–46). 

Neiva: (1PD–5802). 

Sud: Gardan-Horizon (GY–80). 

LaVerda: Falco (F8L Series II, America). 

Malmo: Vipan (MF1–10). 

Kingsford Smith: Autocrat (SCRM–153). 

Aero Commander: 100. 

O–320–A2B .................................... Piper Aircraft: Tri-Pacer (PA–22 ‘‘150’’, PA–22S ‘‘150’’), Cherokee (PA–28 ‘‘150’’), Super Cub (PA–18 

‘‘150’’). 

Champion Aircraft: Challenger (7GCA, 7GCB, 7KC), Citabria (7GCAA, 7GCRC), Agriculture (7GCBA). 

Beagle: Pup (150). 

Artic: Interstate S1B2. 

Robinson: R–22. 

Varga: Kachina 2150A. 

O–320–A2C .................................... Robinson: R–22. 

Cicare: Cicare AG. 

Bellanca Aircraft: Citabria 150 (7GCAA), Citabria 150S (7GCBC). 

O–320–A2D .................................... Piper Aircraft: Apache (PA–23). 

O–320–A3A .................................... Doyn Aircraft: Doyn-Cessna (170, 170A, 170B). 

Corben-Fettes: Globe Special (Globe GC–1B). 

O–320–A3B .................................... Piper Aircraft: Apache (PA–23). 

Doyn Aircraft: Doyn-Cessna (170, 170A, 170B). 

Teal II: TSC (1A2). 

O–320–B1A .................................... Piper Aircraft: Apache (PA–23 ‘‘160’’). 

Doyn Aircraft: Doyn-Cessna (170, 170A, 170B). 

Malmo: Vipan (MF1–10). 

O–320–B1B .................................... Piper Aircraft: Apache (PA–23 ‘‘160’’). 

Doyn Aircraft: Doyn-Cessna (170, 170A, 170B). 

O–320–B2A .................................... Piper Aircraft: Tri-Pacer (PA–22 ‘‘160’’, PA–22S ‘‘160’’). 

O–320–B2B .................................... Piper Aircraft: Tri-Pacer (PA–22 ‘‘160’’, PA–22S ‘‘160’’). 

Beagle: Airedale (D5–160). 

Fuji-Heavy Industries: Fuji (F–200). 

Uirapuru: Aerotec 122. 

O–320–B2C .................................... Robinson: R–22. 

O–320–B2D .................................... Maule: MX–7–160. 

O–320–B2E .................................... Lycon. 

O–320–B3A .................................... Piper Aircraft: Apache (PA–23 ‘‘160’’). 

Doyn Aircraft: Doyn-Cessna (170, 170A, 170B). 

O–320–B3B .................................... Piper Aircraft: Apache (PA–23 ‘‘160’’). 

Doyn Aircraft: Doyn-Cessna (170, 170A, 170B). 

Sud: Gardan (GY80–160). 

O–320–C1A .................................... Piper Aircraft: Apache (PA–23 ‘‘160’’). 

Riley Aircraft: Rayjay (Apache). 

O–320–C1B .................................... Piper Aircraft: Apache (PA–23 ‘‘160’’). 

O–320–C3A .................................... Piper Aircraft: Apache (PA–23 ‘‘160’’). 

O–320–C3B .................................... Piper Aircraft: Apache (PA–23 ‘‘160’’). 

O–320–D1A .................................... Sud: Gardan (GY–80). 

Gyroflug: Speed Cancard. 

Grob: G115. 

O–320–D1F .................................... Slingsby: T67 Firefly. 

O–320–D2A .................................... Piper Aircraft: Cherokee (PA–28S ‘‘160’’). 

Robin: Major (DR400–140B), Chevalier (DR–360), (R–3140). 

S.O.C.A.T.A.: Tampico TB9. 

Slingsby: T67C Firefly. 

Daetwyler: MD–3–160. 

Nash Aircraft Ltd.: Petrel. 

Aviolight: P66D Delta. 

General Avia: Pinguino. 

O–320–D2B .................................... Beech Aircraft: Musketeer (M–23). 

Piper Aircraft: Cherokee (PA–28 ‘‘160’’). 

O–320–D2J ..................................... Cessna Aircraft: Skyhawk 172. 

O–320–D3G .................................... Piper Aircraft: Warrior II, Cadet (PA–28–161). 

O–320–E1A .................................... Grob: G115. 

O–320–E1C .................................... M.B.B. (Messerschmitt-Boelkow-Blohm): Monsun (BO–209–B). 

O–320–E1F .................................... M.B.B.: Monsun (BO–209–B). 

O–320–E2A .................................... Piper Aircraft: Cherokee (PA–28 ‘‘140’’, PA–28 ‘‘150’’). 

Robin: Major (DR–340), Sitar, Bagheera (GY–100–135). 

S.O.C.A.T.A.: Super Rallye (MS–886), Rallye Commodore (MS–892). 

Siai-Marchetti: (S–202). 

F.F.A.: Bravo (AS–202/15). 

Partenavia: Oscar (P66B), Bucker (131 APM). 

Aeromot: Paulistina P–56. 


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TABLE 2—ENGINES INSTALLED ON, BUT NOT LIMITED TO—Continued 

Engine models Installed on, but not limited to 

Pezetel: Koliber 150. 

O–320–E2C .................................... Beech Aircraft: Musketeer III (M–23III). 

M.B.B.: Monsun (BO–209–B). 

O–320–E2D .................................... Cessna Aircraft: Cardinal (172–I, 177). 

O–320–E2F .................................... M.B.B.: Monsun (BO–209–B), Wassmer Pacific (WA–51). 

O–320–E2G .................................... American Aviation Corp.: Traveler. 

O–320–E3D .................................... Piper Aircraft: Cherokee (140). 

Beech Aircraft: Sport. 

IO–320–B2A ................................... Piper Aircraft: Twin Comanche (PA–30). 

IO–320–B1C ................................... Hi. Shear: Wing. 

IO–320–B1D ................................... Ted Smith Aircraft: Aerostar. 

IO–320–C1A ................................... Piper Aircraft: Twin Comanche (PA–30 Turbo). 

IO–320–D1A ................................... M.B.B.: Monsun (BO–209–C). 

IO–320–D1B ................................... M.B.B.: Monsun (BO–209–C). 

IO–320–E1A ................................... M.B.B.: Monsun (BO–209–C). 

IO–320–E1B ................................... Bellanca Aircraft. 

IO–320–E2A ................................... Champion Aircraft: Citabria. 

IO–320–E2B ................................... Bellanca Aircraft. 

IO–320–F1A ................................... CAAR Engineering: Carr Midget. 

LIO–320–B1A ................................. Piper Aircraft: Twin Comanche (PA–39). 

LIO–320–C1A ................................. Piper Aircraft: Twin Comanche (PA–39). 

AIO–320–B1B ................................. M.B.B.: Monsun (BO–209–C). 

AEIO–320–D1B .............................. Slingsby: T67M Firefly. 

AEIO–320–D2B .............................. Hundustan Aeronautics Ltd.: HT–2. 

AEIO–320–E1A .............................. Bellanca Aircraft. 

Champion Aircraft. 

AEIO–320–E1B .............................. Bellanca Aircraft. 

Champion Aircraft: Decathalon (8KCAB–CS). 

AEIO–320–E2B .............................. Bellanca Aircraft. 

Champion Aircraft: Decathalon (8KCAB). 

O–320–A1A .................................... Riley Aircraft: Riley Twin. 

O–360–A1A .................................... Beech Aircraft: Travel Air (95, B–95). 

Piper Aircraft: Comanche (PA–24). 

Intermountain Mfg. Co.: Call Air (A–6). 

Lake Aircraft: Colonial (C–2, LA–4, 4A or 4P). 

Doyn Aircraft: Doyn-Cessna (170B, 172, 172A, 172B). 

Mooney Aircraft: Mark ‘‘20B’’ (M–20B). 

Earl Horton: Pawnee (Piper PA–25). 

Dinfia: Ranquel (1A–51). 

Neiva: (1PD–5901). 

Regente: (N–591). 

Wassmer: Super 4 (WA–50A), Sancy (WA–40), Baladou (WA–40), Pariou (WA–40). 

Sud: Gardan (GY–180). 

Boelkow: (207). 

Partenavia: Oscar (P–66). 

Siai-Marchetti: (S–205). 

Procaer: Picchio (F–15–A). 

S.A.A.B.: Safir (91–D). 

Malmo: Vipan (MF–10B). 

Aero Boero: AB–180. 

Beagle: Airedale (A–109). 

DeHavilland: Drover (DHA–3MK3). 

Kingsford-Smith: Bushmaster (J5–6). 

Aero Engine Service Ltd.: Victa (R–2). 

O–360–A1AD .................................. S.O.C.A.T.A.: Tabago TB–10. 

O–360–A1D .................................... Piper Aircraft: Comanche (PA–24). 

Lake Aircraft: Colonial (LA–4, 4A or 4P). 

Doyn Aircraft: Doyn-Beech (Beech 95). 

Mooney Aircraft: Master ‘‘21’’ (M–20E), Mark ‘‘20B’’, ‘‘20D’’, (M20B, M20C), Mooney Statesman (M–20G). 

Dinfia: Querandi (1A–45). 

Wassmer: (WA–50). 

Malmo: Vipan (MF1–10). 

Cessna Aircraft: Skyhawk. 

Doyn Aircraft: Doyn-Piper (PA–23 ‘‘160’’). 

O–360–A1F6 .................................. Cessna Aircraft: Cardinal. 

O–360–A1F6D ................................ Cessna Aircraft: Cardinal 177. 

Teal III: TSC (1A3). 

O–360–A1G6 .................................. Aero Commander. 

O–360–A1G6D ............................... Beech Aircraft: Duchess 76. 

O–360–A1H6 .................................. Piper Aircraft: Seminole (PA–44). 

O–360–A1LD .................................. Wassmer: Europa WA–52. 

O–360–A1P .................................... Aviat: Husky. 


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37960 Federal Register / Vol. 74, No. 145 / Thursday, July 30, 2009 / Proposed Rules 

TABLE 2—ENGINES INSTALLED ON, BUT NOT LIMITED TO—Continued 

Engine models Installed on, but not limited to 

O–360–A2A .................................... Center Est Aeronautique: Regente (DR–253). 

S.O.C.A.T.A.: Rallye Commodore (MS–893). 

Societe Aeronautique Normande: Mousquetaire (D–140). 

Boelkow: Klemm (K1–107C). 

Partenavia: Oscar (P–66). 

Beagle: Husky (D5–180) (J1–U). 

O–360–A2D .................................... Piper Aircraft: Comanche (PA–24), Cherokee ‘‘C’’ (PA–28 ‘‘180’’). 

Mooney Aircraft: Master ‘‘21’’ (M–20D), Mark ‘‘21’’ (M–20E). 

O–360–A2E .................................... Std. Helicopter. 

O–360–A2F .................................... Aero Commander: Lark (100). 

Cessna Aircraft: Cardinal. 

O–360–A2G .................................... Beech Aircraft: Sport. 

O–360–A3A .................................... C.A.A.R.P.S.A.N.: (M–23III). 

Societe Aeronautique Normande: Jodel (D–140C). 

Robin: Regent (DR400/180), Remorqueur (DR400/180R), R–3170. 

S.O.C.A.T.A.: Rallye 180GT, Sportavia Sportsman (RS–180). 

Norman Aeroplace Co.: NAC–1 Freelance. 

Nash Aircraft Ltd.: Petrel. 

O–360–A3AD .................................. S.O.C.A.T.A.: TB–10. 

Robin: Aiglon (R–1180T). 

O–360–A4A .................................... Piper Aircraft: Cherokee ‘‘D’’ (PA–28 ‘‘180’’). 

O–360–A4D .................................... Varga: Kachina. 

O–360–A4G .................................... Beech Aircraft: Musketeer Custom III. 

O–360–A4K .................................... Grumman American: Tiger. 

Beech Aircraft: Sundowner 180. 

O–360–A4M .................................... Piper Aircraft: Archer II (PA–28 ‘‘18’’). 

Valmet: PIK–23. 

O–360–A4N .................................... Cessna Aircraft: 172 (Optional). 

O–360–A4P .................................... Penn Yan: Super Cub Conversion. 

O–360–A5AD .................................. C. Itoh and Co.: Fuji FA–200. 

O–360–B2C .................................... Seabird Aviation: SB7L. 

O–360–C1A .................................... Intermountain Mfg. Co.: Call Air (A–6). 

O–360–C1E .................................... Bellanca Aircraft: Scout (8GCBC–CS). 

O–360–C1F .................................... Maule: Star Rocket MX–7–180. 

O–360–C1G .................................... Christen: Husky (A–1). 

O–360–C2B .................................... Hughes Tool Co.: (269A). 

O–360–C2D .................................... Hughes Tool Co.: (269A). 

O–360–C2E .................................... Hughes Tool Co.: (YHO–2HU) Military. 

Bellanca Aircraft: Scout (8GCBC FP). 

O–360–C4F .................................... Maule: MX–7–180A. 

O–360–C4P .................................... Penn Yan: Super Cub Conversion. 

O–360–F1A6 .................................. Cessna Aircraft: Cutlass RG. 

O–360–J2A ..................................... Robinson: R22. 

IO–360–B1A ................................... Beech Aircraft: Travel-Air (B–95A). 

Doyn Aircraft: Doyn-Piper (PA–23 ‘‘200’’). 

IO–360–B1B ................................... Beech Aircraft: Travel-Air (B–95B). 

Doyn Aircraft: Doyn-Piper (PA–23 ‘‘200’’). 

Fuji: (FA–200). 

IO–360–B1D ................................... United Consultants: See-Bee. 

IO–360–B1E ................................... Piper Aircraft: Arrow (PA–28 ‘‘180R’’). 

IO–360–B1F ................................... Utva: 75. 

IO–360–B2E ................................... C.A.A.R.P. C.A.P. (10). 

IO–360–B1F6 ................................. Great Lakes: Trainer. 

IO–360–B1G6 ................................. American Blimp: Spector 42. 

IO–360–B2F6 ................................. Great Lakes: Trainer. 

LO–360–A1G6D ............................. Beech Aircraft: Duchess. 

LO–360–A1H6 ................................ Piper Aircraft: Seminole (PA–44). 

IO–360–E1A ................................... T.R. Smith Aircraft: Aerostar. 

IO–360–L2A .................................... Cessna Aircraft: Skyhawk C–172. 

IO–360–M1A ................................... Diamond Aircraft: DA–40. 

IO–360–M1B ................................... Vans Aircraft: RV6, RV7, RV8. 

Lancair: 360. 

AEIO–360–B1F ............................... F.F.A.: Bravo (200). 

Grob: G115/Sport-Acro. 

AEIO–360–B1G6 ............................ Great Lakes. 

AEIO–360–B2F ............................... Mundry: CAP–10. 

AEIO–360–B4A .............................. Pitts: S–1S. 

AEIO–360–H1A .............................. Bellanca Aircraft: Super Decathalon (8KCAB–180). 

AEIO–360–H1B .............................. American Champion: Super Decathalon. 

VO–360–A1A .................................. Brantly Hynes Helicopter: (B–2). 

VO–360–A1B .................................. Brantly Hynes Helicopter: (B–2, B2–A). Military (YHO–3BR). 

VO–360–B1A .................................. Brantly Hynes Helicopter: (B–2, B2–A). 


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Federal Register / Vol. 74, No. 145 / Thursday, July 30, 2009 / Proposed Rules 37961 

TABLE 2—ENGINES INSTALLED ON, BUT NOT LIMITED TO—Continued 

Engine models Installed on, but not limited to 

IVO–360–A1A ................................. Brantly Hynes Helicopter: (B2–B). 

HO–360–B1A .................................. Hughes Tool Co.: (269A). 

HO–360–B1B .................................. Hughes Tool Co.: (269A). 

HO–360–C1A ................................. Schweizer: (300C). 

HIO–360–B1A ................................. Hughes Tool Co.: Military (269–A–1), (TH–55A). 

HIO–360–B1B ................................. Hughes Tool Co.: (269A). 

HIO–360–G1A ................................ Schweizer: (CB). 

O–540–A1A .................................... Rhein-Flugzeugbau: (RF–1). 

O–540–A1A5 .................................. Piper Aircraft: Comanche (PA–24 ‘‘180’’). 

Helio: Military (H–250). 

Yoeman Aviation: (YA–1). 

O–540–A1B5 .................................. Piper Aircraft: Aztec (PA–23 ‘‘250’’), Comanche (PA–24 ‘‘250’’). 

O–540–A1C5 .................................. Piper Aircraft: Comanche (PA–24 ‘‘250’’). 

O–540–A1D .................................... Found Bros.: (FBA–2C). 

Dornier: (DO–28–B1). 

O–540–A1D5 .................................. Piper Aircraft: Aztec (PA–23 ‘‘250’’), Comanche (PA–24 ‘‘250’’), Military Aztec (U–11A). 

Dornier: (DO–28). 

O–540–A2B .................................... Aero Commander: (500). 

Mid-States Mfg. Co.: Twin Courier (H–500), (U–5). 

O–540–A3D5 .................................. Piper Aircraft: Navy Aztec (PA–23 ‘‘250’’). 

O–540–B1A5 .................................. Piper Aircraft: Apache (PA–23 ‘‘235’’). 

O–540–B1B5 .................................. Piper Aircraft: Comanche (PA–24 ‘‘250’’). 

Doyn Aircraft: Doyn-Piper (PA–24 ‘‘250’’). 

O–540–B1D5 .................................. Wassmer: (WA–421). 

O–540–B2B5 .................................. Piper Aircraft: Pawnee (PA–25 ‘‘235’’), Cherokee (PA–28 ‘‘235’’), Aztec (PA–23 ‘‘235’’). 

Intermountain Mfg. Co.: Call Air (A–9). 

Rawdon Bros.: Rawdon (T–1). 

S.O.C.A.T.A.: Rallye 235CA. 

O–540–B2C5 .................................. Piper Aircraft: Pawnee (PA–25 ‘‘235’’). 

O–540–B4B5 .................................. Piper Aircraft: Cherokee (PA–28 ‘‘235’’). 

Embraer: Corioca (EMB–710). 

S.O.C.A.T.A.: Rallye 235GT, Rallye 235C. 

Maule: Star Rocket (MX–7–235), Super Rocket (M–6–235), Super Std. Rocket (M–7–235). 

O–540–E4A5 .................................. Piper Aircraft: Comanche (PA–24 ‘‘260’’). 

Aviamilano: Flamingo (F–250). 

Siai-Marchetti: (SF–260), (SF–208). 

O–540–E4B5 .................................. Britten-Norman: (BN–2). 

Piper Aircraft: Cherokee Six (PA–32 ‘‘260’’). 

O–540–E4C5 .................................. Pilatus Britten-Norman: Islander (BN–2A–26), Islander (BN–2A–27), Islander II (BN–2B–26), Islander (BN– 

2A–21), Trislander (BN–2A–Mark III–2). 

O–540–F1B5 .................................. Omega Aircraft: (BS–12D1). 

Robinson: (R–44). 

O–540–G1A5 .................................. Piper Aircraft: Pawnee (PA–25 ‘‘260’’). 

O–540–H1B5D ............................... Aero Boero: 260. 

O–540–H2A5 .................................. Embraer: Impanema ‘‘AG’’. 

Gippsland: GA–200. 

O–540–H2B5D ............................... Aero Boero: 260. 

O–540–J1A5D ................................ Maule: Star Rocket (MX–7–235), Super Rocket (M–6–235), Super Std. Rocket (M–7–235). 

O–540–J3A5 ................................... Robin: R–3000/235. 

O–540–J3A5D ................................ Piper Aircraft: Dakota (PA–28–236). 

O–540–J3C5D ................................ Cessna Aircraft: Skylane RG. 

O–540–L3C5D ................................ Cessna Aircraft: TR–182, Turbo Skylane RG. 

IO–540–C1B5 ................................. Piper Aircraft: Aztec B (PA–23 ‘‘250’’), Comanche (PA–24 ‘‘250’’). 

IO–540–C1C5 ................................. Riley Aircraft: Turbo-Rocket. 

IO–540–C4B5 ................................. Piper Aircraft: Aztec C (PA–23 ‘‘250’’), Aztec F. 

Wassmer: (WA4–21). 

Avions Pierre Robin: (HR100/250). 

Bellanca Aircraft: Aries T–250. 

Aerofab: Renegade 250. 

IO–540–C4D5 ................................. S.O.C.A.T.A.: TB–20. 

IO–540–C4D5D .............................. S.O.C.A.T.A.: Trinidad TB–20. 

IO–540–D4A5 ................................. Piper Aircraft: Comanche (PA–24 ‘‘260’’). 

Siai-Marchetti: (SF–260). 

IO–540–D4B5 ................................. Cerva: (CE–43 Guepard). 

IO–540–J4A5 .................................. Piper Aircraft: Aztec (PA–23 ‘‘250’’). 

IO–540–R1A5 ................................. Piper Aircraft: Comanche (PA–24). 

IO–540–T4A5D ............................... General Aviation: Model 114. 

IO–540–T4B5 ................................. Commander: 114B. 

IO–540–T4B5D ............................... Rockwell: 114. 

IO–540–T4C5D ............................... Lake Aircraft: Seawolf. 

IO–540–V4A5 ................................. Maule: MT–7–260, M–7–260. 

Aircraft Manufacturing Factory. 


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37962 Federal Register / Vol. 74, No. 145 / Thursday, July 30, 2009 / Proposed Rules 

TABLE 2—ENGINES INSTALLED ON, BUT NOT LIMITED TO—Continued 

Engine models Installed on, but not limited to 

IO–540–V4A5D ............................... Brooklands: Scoutmaster. 

IO–540–W1A5 ................................ Maule: MX–7–235, MT–7–235, M7–235. 

IO–540–W1A5D .............................. Maule: Star Rocket (MX–7–235), Super Rocket (M–6–235), Super Std. Rocket (M–7–235). 

IO–540–W3A5D .............................. Schweizer: Power Glider. 

AEIO–540–D4A5 ............................ Christen: Pitts (S–2S), (S–2B). 

Siai-Marchetti: SF–260. 

H.A.L.: HPT–32. 

Slingsby: Firefly T3A. 

AEIO–540–D4B5 ............................ Moravan: Zlin-50L. 

H.A.L.: HPT–32. 

AEIO–540–D4D5 ............................ Burkhart Grob: Grob G, 115T Aero. 

TIO–540–C1A ................................. Piper Aircraft: Turbo Aztec (PA–23–250). 

TIO–540–K1AD .............................. Piper Aircraft. 

TIO–540–AA1AD ............................ Aerofab Inc.: Turbo Renegade (270). 

TIO–540–AB1AD ............................ S.O.C.A.T.A.: Trinidad TC TB–21. 

TIO–540–AB1BD ............................ Schweizer. 

TIO–540–AF1A ............................... Mooney Aircraft: ‘‘TLS’’ M20M. 

TIO–540–AG1A .............................. Commander Aircraft: 114TC. 

TIO–540–AK1A ............................... Cessna Aircraft: Turbo Skylane T182T. 

LTIO–540–K1AD ............................ Piper Aircraft. 

Unsafe Condition 

(e) This AD results from reports of 10 

additional cylinder head separations since 

issuing AD 2008–19–05, on cylinder serial 

numbers not listed in that AD. We are issuing 

this AD to prevent loss of engine power due 

to cracks at the head-to-barrel interface in the 

cylinder assemblies and possible engine 

failure caused by separation of a cylinder 

head, which could result in loss of control of 

the aircraft. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified unless the 

actions have already been done. 

Engines Overhauled or Cylinder Assemblies 

Replaced Since New 

(g) If your engine was overhauled or had 

a cylinder assembly replaced since new, do 

the following: 

(1) Before further flight, inspect the 

maintenance records and engine logbook to 

determine if the overhaul or repair facility 

used ECi cylinder assemblies, P/N 

AEL65102, with cylinder head, PN 

AEL85099, with a SN 1138–02 through SN 

35171–22, or a SN 35239–01 through SN 

42179–30, installed. 

(2) If the cylinder assemblies are not ECi, 

P/N AEL65102, no further action is required. 

(3) If the cylinder assemblies are ECi, P/N 

AEL65102, and if the SN is not listed in this 

AD, no further action is required. 

(4) If the cylinder assemblies are ECi, P/N 

AEL65102, and if the SN is listed in this AD, 

do the following: 

Group ‘‘A’’ Cylinder Assemblies 

(i) For Group ‘‘A’’ cylinder assemblies: 

(A) Perform an initial visual inspection as 

specified in paragraphs (h) through (i) of this 

AD, and an initial compression test as 

specified in paragraphs (j) through (n) of this 

AD, within the next 10 operating hours timein-service (TIS), if the cylinder assembly has 

350 or more operating hours TIS on the 

effective date of this AD, but fewer than 

2,000 operating hours TIS. 

(B) Perform an initial visual inspection as 

specified in paragraphs (h) through (i) of this 

AD, and an initial compression test as 

specified in paragraphs (j) through (n) of this 

AD, within the next 10 operating hours TIS, 

or before exceeding 350 operating hours TIS, 

whichever occurs later, if the cylinder 

assembly has fewer than 350 operating hours 

TIS on the effective date of this AD. 

(C) Replace cylinder assemblies installed 

in helicopter engines within the next 25 

operating hours TIS after the effective date of 

this AD if the cylinder assembly has 1,500 

operating hours TIS or more on the effective 

date of this AD. 

(D) Replace cylinder assemblies installed 

in airplane engines within the next 25 

operating hours TIS after the effective date of 

this AD if the cylinder assembly has 2,000 

operating hours TIS or more on the effective 

date of this AD. 

(E) Perform repetitive visual inspections as 

specified in paragraphs (h) through (i) of this 

AD, and repetitive compression tests as 

specified in paragraphs (j) through (n) of this 

AD, within every 50 operating hours TIS. 

(F) Replace cylinder assemblies installed in 

helicopter engines that pass the visual 

inspections and compression tests, no later 

than 1,500 operating hours TIS after the 

effective date of this AD. 

(G) Replace cylinder assemblies installed 

in airplane engines that pass the visual 

inspections and compression tests, no later 

than 2,000 operating hours TIS after the 

effective date of this AD. 

Group ‘‘B’’ Cylinder Assemblies 

(ii) For Group ‘‘B’’ cylinder assemblies: 

(A) Perform an initial visual inspection as 

specified in paragraphs (h) through (i) of this 

AD, and initial compression test as specified 

in paragraphs (j) through (n) of this AD, 

within the next 10 operating hours TIS. 

(B) Replace the cylinder assembly within 

the next 25 operating hours TIS after the 

effective date of this AD if the cylinder 

assembly has 350 or more operating hours 

TIS on the effective date of this AD. 

(C) Replace cylinder assemblies that pass 

the initial visual inspections and 

compression tests, before exceeding 350 

operating hours TIS after the effective date of 

this AD. 

Visual Inspection 

(h) Visually inspect each cylinder head 

around the exhaust valve side for cracks or 

any signs of black or white residue of 

combustion leakage from cracks. 

(i) Replace cracked cylinder assemblies 

before further flight. 

Cylinder Assembly Compression Test 

(j) Perform a standard cylinder differential 

compression test. 

(k) During the compression test, if the 

cylinder pressure gauge reads below 70 

pounds-per-square-inch, apply a water and 

soap solution to the side of the leaking 

cylinder, near the head-to-barrel interface. 

(l) Replace the cylinder assembly before 

further flight if air leakage and bubbles are 

observed on the side of the cylinder 

assembly, near the head-to-barrel interface. 

(m) Repair or replace the engine cylinder 

assembly before further flight if the cause of 

the low gauge reading in paragraph (l) of this 

AD is from leaking intake or exhaust valves, 

or from leaking piston rings. 

Prohibition of ECi Cylinder Assemblies 

Affected by This AD 

(n) After the effective date of this AD, do 

not install any ECi cylinder assembly, P/N 

AEL65102, with cylinder head, P/N 

AEL85099, and with SN 1138–02 through SN 

35171–22, or SN 35239–01 through SN 

42179–30, onto any engine, and do not 

attempt to repair or reuse these ECi cylinder 

assemblies. 

Alternative Methods of Compliance 

(o) The Manager, Special Certification 

Office, has the authority to approve 

alternative methods of compliance for this 


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Federal Register / Vol. 74, No. 145 / Thursday, July 30, 2009 / Proposed Rules 37963 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Special Flight Permits 

(p) Under 14 CFR part 39.23, we will not 

approve special flight permits for this AD for 

engines that have failed the visual inspection 

or the cylinder assembly compression test 

required by this AD. 

Related Information 

(q) Contact Peter W. Hakala, Aerospace 

Engineer, Special Certification Office, FAA, 

Rotorcraft Directorate, 2601 Meacham Blvd., 

Fort Worth, TX 76193; e-mail: 

peter.w.hakala@faa.gov; telephone (817) 

222–5145; fax (817) 222–5785, for more 

information about this AD. 

Issued in Burlington, Massachusetts, on 

July 21, 2009. 

Peter A. White, 

Assistant Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–18118 Filed 7–29–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0658; Directorate 

Identifier 2009–NM–058–AD] 

RIN 2120–AA64 

Airworthiness Directives; McDonnell 

Douglas Model DC–9–14, DC–9–15, 

and DC–9–15F Airplanes; and 

McDonnell Douglas Model DC–9–20, 

DC–9–30, DC–9–40, and DC–9–50 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) that applies to all 

McDonnell Douglas Model DC–9–14, 

DC–9–15, and DC–9–15F airplanes; and 

McDonnell Douglas Model DC–9–20, 

DC–9–30, DC–9–40, and DC–9–50 series 

airplanes. The existing AD currently 

requires repetitive inspections for cracks 

of the main landing gear (MLG) shock 

strut cylinder, and related investigative 

and corrective actions if necessary. This 

proposed AD would add more work on 

airplanes that have main landing gear 

shock struts with certain identified part 

numbers. This proposed AD results 

from two reports of a collapsed MLG 

and a report of cracks in two MLG 

cylinders. We are proposing this AD to 

detect and correct fatigue cracks in the 

shock strut cylinder of the MLG, which 

could result in a collapsed MLG during 

takeoff or landing, and possible reduced 

structural integrity of the airplane. 

DATES: We must receive comments on 

this proposed AD by September 14, 

2009. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue, SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221 or 425–227–1152. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Wahib Mina, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; telephone (562) 

627–5324; fax (562) 627–5210. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2009–0658; Directorate Identifier 

2009–NM–058–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On September 7, 2005, we issued AD 

2005–19–08, amendment 39–14273 (70 

FR 54616, September 16, 2005), for all 

McDonnell Douglas Model DC–9–14, 

DC–9–15, and DC–9–15F airplanes; and 

McDonnell Douglas Model DC–9–20, 

DC–9–30, DC–9–40, and DC–9–50 series 

airplanes. That AD requires repetitive 

inspections for cracks of the main 

landing gear (MLG) shock strut cylinder, 

and related investigative and corrective 

actions if necessary. That AD resulted 

from two reports of a collapsed MLG 

and a report of cracks in two MLG 

cylinders. We issued that AD to detect 

and correct fatigue cracks in the shock 

strut cylinder of the MLG, which could 

result in a collapsed MLG during takeoff 

or landing, and possible reduced 

structural integrity of the airplane. 

Actions Since Existing AD Was Issued 

Since we issued AD 2005–19–08, the 

manufacturer revised the service 

information referenced in that AD, i.e., 

Boeing Alert Service Bulletin DC9– 

32A350, Revision 1, dated August 3, 

2005, to add more work on airplanes 

that have shock struts with part 

numbers 5924400–505 and 5924400– 

506. 

Relevant Service Information 

We have reviewed Boeing Alert 

Service Bulletin DC9–32A350, Revision 

2, dated March 20, 2009, which 

specifies that shock struts having part 

numbers 5924400–505 and 5924400– 

506 must be included with those struts 

that require repetitive non-destructive 

testing inspections. The remaining 

actions are otherwise unchanged. 

FAA’s Determination and Requirements 

of the Proposed AD 

We have evaluated all pertinent 

information and identified an unsafe 


erowe on DSK5CLS3C1PROD with PROPOSALS-1