54618 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations 

determine its service history and the number 

of landings on the MLG shock strut cylinder. 

(2) For Group 3 airplanes identified in the 

service bulletin: Review the maintenance 

records to determine if the MLG cylinder on 

each Group 3 airplane has always been on a 

Group 3 airplane, and do the actions in 

paragraph (k) of this AD. 

Inspection 

(h) Inspect the MLG shock strut cylinders 

for cracks using the Option 1 or Option 2 

non-destructive testing inspection described 

in the service bulletin. Inspect in accordance 

with the Accomplishment Instructions of the 

service bulletin. Do the detailed inspection 

before the accumulation of 60,000 total 

landings on the MLG, or at the applicable 

grace period specified in Table 1 of this AD, 

whichever occurs later, except as provided 

by paragraph (k) of this AD. If the review of 

maintenance records is not sufficient to 

conclusively determine the service history 

and number of landings on the MLG shock 

strut cylinder, perform the initial inspection 

at the applicable grace period specified in 

Table 1 of this AD. 

TABLE 1.—GRACE PERIOD AND REPETITIVE INTERVAL

Airplanes identified in the service bulletin as 

group Grace period Repetitive interval 

1 ......................................................................... Within 18 months or 650 landings after the effective date of this AD, whichever occurs 

first.

Intervals not to exceed 650 landings. 

2 ......................................................................... Within 18 months or 500 landings after the effective date of this AD, whichever occurs 

first.

Intervals not to exceed 500 landings. 

3, except as provided by paragraph (k) of this 

AD.

Within 18 months or 2,500 landings after the 

effective date of this AD, whichever occurs 

first.

Intervals not to exceed 2,500 landings. 

4 ......................................................................... Within 18 months or 2,100 landings after the 

effective date of this AD, whichever occurs 

first.

Intervals not exceed 2,100 landings. 

No Crack Indication Found 

(i) If no crack indication is found during 

the inspection required by paragraph (h) of 

this AD, repeat the inspection at the 

applicable interval specified in Table 1 of 

this AD. 

Related Investigative and Corrective Actions 

(j) If any crack indication is found during 

any inspection required by paragraph (h) or 

(i) of this AD, before further flight: Confirm 

the crack indication by doing all applicable 

related investigative actions and doing the 

applicable corrective actions in accordance 

with the service bulletin. Repeat the 

inspection at the applicable threshold and 

interval specified in paragraph (h) of this AD. 

MLG Cylinder Previously Installed on Group 

4 Airplanes 

(k) For MLG cylinders on Group 3 

airplanes as identified in the service bulletin: 

If the MLG cylinder was previously installed 

on a Group 4 airplane, as identified in the 

service bulletin, or if the service history and 

number of landings cannot be determined, 

the MLG cylinder must be inspected at the 

grace period and repetitive interval that 

applies to Group 4 airplanes, as specified in 

Table 1 of this AD. 

Actions Accomplished in Accordance With 

Original Issue of Service Bulletin 

(l) Actions done before the effective date of 

this AD in accordance with Boeing Alert 

Service Bulletin DC9–32A350, dated 

December 3, 2004, are acceptable for 

compliance with the corresponding actions 

required by this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(m) The Manager, Los Angeles Aircraft 

Certification Office, FAA, has the authority to 

approve AMOCs for this AD, if requested in 

accordance with the procedures found in 14 

CFR 39.19. 

Material Incorporated by Reference 

(n) You must use Boeing Alert Service 

Bulletin DC9–32A350, Revision 1, dated 

August 3, 2005, to perform the actions that 

are required by this AD, unless the AD 

specifies otherwise. The Director of the 

Federal Register approved the incorporation 

by reference of this document in accordance 

with 5 U.S.C. 552(a) and 1 CFR part 51. 

Contact Boeing Commercial Airplanes, Long 

Beach Division, 3855 Lakewood Boulevard, 

Long Beach, California 90846, Attention: 

Data and Service Management, Dept. C1–L5A 

(D800–0024), for a copy of this service 

information. You may review copies at the 

Docket Management Facility, U.S. 

Department of Transportation, 400 Seventh 

Street SW., room PL–401, Nassif Building, 

Washington, DC; on the Internet at http:// 

dms.dot.gov; or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at the NARA, call (202) 741–6030, 

or go to http://www.archives.gov/federalregister/cfr/ibr-locations.html. 

Issued in Renton, Washington, on 

September 7, 2005. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–18314 Filed 9–15–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21864; Directorate 

Identifier 2005–NE–29–AD; Amendment 39–

14276; AD 2005–19–11] 

RIN 2120–AA64 

Airworthiness Directives; Lycoming 

Engines (Formerly Textron Lycoming) 

AEIO–360, IO–360, O–360, LIO–360, 

LO–360, AEIO–540, IO–540, O–540, and 

TIO–540 Series Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for certain 

Lycoming Engines (formerly Textron 

Lycoming) AEIO–360, IO–360, O–360, 

LIO–360, LO–360, AEIO–540, IO–540, 

O–540, and TIO–540 series 

reciprocating engines rated at 300 

horsepower (HP) or lower. This AD 

requires replacing certain crankshafts. 

This AD results from reports of 12 

crankshaft failures in Lycoming 360 and 

540 series engines rated at 300 HP or 

lower. We are issuing this AD to prevent 

failure of the crankshaft, which could 

result in total engine power loss, inflight engine failure, and possible loss of 

the aircraft. 

DATES: This AD becomes effective 

October 21, 2005. The Director of the 

Federal Register approved the 

incorporation by reference of certain 

Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations 54619 

publications listed in the regulations as 

of October 21, 2005. 

ADDRESSES: You can get the service 

information identified in this AD from 

Lycoming, 652 Oliver Street, 

Williamsport, PA 17701; telephone 

(570) 323–6181; fax (570) 327–7101, or 

on the Internet at http:// 

www.Lycoming.Textron.com. 

You may examine the AD docket on 

the Internet at http://dms.dot.gov or in 

Room PL–401 on the plaza level of the 

Nassif Building, 400 Seventh Street, 

SW., Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Norm Perenson, Aerospace Engineer, 

New York Aircraft Certification Office, 

FAA, Engine & Propeller Directorate, 

1600 Stewart Avenue, Suite 410, 

Westbury, NY 11590; telephone (516) 

228–7337; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 with 

a proposed airworthiness directive (AD). 

The proposed AD applies to Lycoming 

Engines (formerly Textron Lycoming) 

AEIO–360, IO–360, O–360, LIO–360, 

LO–360, AEIO–540, IO–540, O–540, and 

TIO–540 series reciprocating engines 

rated at 300 horsepower (HP) or lower. 

We published the proposed AD in the 

Federal Register on July 22, 2005 (70 FR 

42282). That action proposed to require 

replacing certain crankshafts within 50 

hours time-in-service or 6 months after 

the effective date of the proposed AD, 

whichever is earlier. 

Examining the AD Docket 

You may examine the docket that 

contains the AD, any comments 

received, and any final disposition in 

person at the Docket Management 

Facility Docket Offices between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Office (telephone (800) 647–5227) is 

located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments received. 

Will Additional Engines and 

Crankshafts Be Affected in the Future 

One commenter asks if additional 

serial numbered engines and 

crankshafts will be affected in the 

future. 

At this time we do not anticipate that 

the affected population will increase, 

but Lycoming and the FAA are 

monitoring crankshaft performance. 

Affected Engines and Crankshafts 

The same commenter asks why these 

engines and crankshafts are the only 

ones affected by the SB and AD. 

Both the previous AD (2002–19–03) 

and this AD advise that the affected 

population of engines and crankshafts 

were manufactured in a specific time 

period. We are addressing that time 

period. 

Suspect Crankshafts Should Be Either 

Tested or Replaced 

One commenter states that suspect 

crankshafts should be either tested or 

replaced before further flight, because 

the problem with these crankshafts is 

similar to the problem that caused the 

crankshaft failures on the 540 engines. 

We disagree. The compliance interval 

in this AD is based on an assessment of 

operating stresses, service experience, 

and duty cycle of the affected engine 

population. The compliance interval 

differs from that imposed in AD 2002–

19–03 due to differences in these 

parameters. 

Request To Include Lycoming TIO–540–

AE2A and Other Unspecified Engine 

Models 

One commenter requests that we 

include the Lycoming TIO–540–AE2A 

and other unspecified engine models in 

this AD. The commenter states that 

many of the TIO–540–AE2A engines 

have never been recalled or replaced yet 

should be, because recent litigation has 

shown that Lycoming’s crankshaft end 

core sample test is insufficient. 

We disagree. We have seen no 

evidence that refutes the validity of the 

test. Further, AD 2002–19–03 (the 

previous AD) effective on September 20, 

2002, described two groups of 

crankshafts. We required one crankshaft 

group to be removed before further 

flight, and we required the other 

crankshaft group to have a sample of the 

crankshaft material tested. The 

crankshafts in each group were selected 

based on our evaluation of the risk both 

groups presented. Crankshafts from 

either group may be installed in the 

TIO–540–AE2A engine model. No 

failures of crankshafts listed in either 

group have occurred since. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

received, and determined that air safety 

and the public interest require adopting 

the AD as proposed. 

Costs of Compliance 

We estimate that this AD will affect 

1,128 engines installed on aircraft of 

U.S. registry. We estimate that it will 

take the following work hours to 

perform the inspection: 

Type of 

application 

Work-hours 

per engine 

Number of 

engines 

affected 

Helicopter ........ 12 200 

ConstantSpeed Propeller ........... 3 557 

Fixed-Pitch 

Propeller ...... 1 .5 371 

We also estimate that it will take 

about 33 work hours to replace the 

crankshaft. We estimate the average 

labor rate is $65 per work hour and that 

required parts for each engine will cost 

about $16,218. Based on these figures, 

we estimate the total cost of the AD to 

U.S. operators to be $18,594,724. 

Lycoming Engines informed us that they 

intend to supply the new parts at no 

charge, which may substantially reduce 

the estimated cost of this AD. 

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 AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

54620 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

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

(3) Will 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 summary of the costs 

to comply with this AD and placed it in 

the AD Docket. You may get a copy of 

this summary at the address listed 

under ADDRESSES. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends 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 adding 

the following new airworthiness 

directive: 

2005–19–11 Lycoming Engines: 

Amendment 39–14276. Docket No. 

FAA–2005–21864; Directorate Identifier 

2005–NE–29–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective October 21, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Lycoming Engines 

(Formerly Textron Lycoming) AEIO–360, IO–

360, O–360, LIO–360, LO–360, AEIO–540, 

IO–540, O–540, and TIO–540 series 

reciprocating engines, rated at 300 

horsepower (HP) or lower, manufactured 

new, rebuilt, overhauled after March 1, 1999, 

or that had a crankshaft installed after March 

1, 1999. These engines are installed on, but 

not limited to, the following aircraft: 

Engine model Manufacturer Aircraft model 

IO–540–V4A5 ..................................................... A.M.F ................................................................ 17–D Mushshak 

Aero Commander ............................................. 500 B, S, U/Merlyn Products Conv. 

IO–540–E1A5 ..................................................... Aero Commander ............................................. 500–E 

Aerofab ............................................................. LA 250 Renegade 

Aeronautica ...................................................... Agricola Mexicana Quail 

IO–540–K1F5 ..................................................... Aerostar ............................................................ 600 

Aircraft Manufacturing Factory ......................... Mushshak 

O–540–E4A5 ...................................................... Aviamilano ........................................................ F–250 Flamingo 

IO–540–C4B5 .................................................... Avions ............................................................... Pierre Robin HR–100/250 

LO–360–A1G6D ................................................. Beech ............................................................... 76 Duchess 

O–360–A1G6D ................................................... ........................................................................... 76 Duchess 

C–24R Sierra or 200 Sierra 

Bellanca ............................................................ Aircraft Aries T–250 

O–540–E4B5 ...................................................... Britten Norman ................................................. BN–2 Islander 

O–540–E4C5 ..................................................... ........................................................................... BN–2A & BN–2B Islander 

IO–540–K1B5 ..................................................... ........................................................................... BN–2A Islander 

Celair ................................................................ Eagle 

O–360–A1F6 ...................................................... Cessna ............................................................. 177 Cardinal 

O–360–A1F6D ................................................... ........................................................................... 177 Cardinal 

O–540–J3C5D ................................................... ........................................................................... 182–RG Skylane 

IO–540–AB1A5 .................................................. ........................................................................... 182–S 

O–360–F1A6 ...................................................... ........................................................................... C–172RG Cutlass RG 

IO–540–AC1A5 .................................................. ........................................................................... C–206 Stationair 

R–G Cardinal 

IO–360–A1B6D .................................................. ........................................................................... R–G Cardinal 

TIO–540–AK1A .................................................. ........................................................................... T182T Skylane 

O–540–L3C5D ................................................... ........................................................................... TR–182 Turbo Skylane 

AEIO–540–D4A5 ................................................ Christen Pitts .................................................... S–2S, S–2B 

IO–540–T4B5D .................................................. Commander ...................................................... 114 

IO–540–T4B5 ..................................................... ........................................................................... 114B 

TIO–540–AG1A .................................................. ........................................................................... 114TC 

Dornier .............................................................. DO–28 

IO–540–K1J5D ................................................... Embraer ............................................................ EMB–201 Ipanema 

O–540–B4B5 ...................................................... ........................................................................... EMB–710 Corioca 

EMB–720 Minuano 

EMB–720 Minuano & EMB–721 Sertanejo 

EMB–721 Sertanejo 

AEIO–540–L1B5 ................................................ Extra-Flugzeugbau ........................................... Extra 300 

F.F.A ................................................................. FFA–2000 Eurotrainer 

H.A.L ................................................................ HPT–32 

O–540–A1A5 ...................................................... Helio Military ..................................................... H–250 

AEIO–360–A1E6 ................................................ Integrated Systems .......................................... Omega 

IO–540–M1C5 .................................................... King Engineering .............................................. Angel 

Korean Air ........................................................ Chang Gong–91 

Lake .................................................................. LA–4–200 Buccaneer 

O–540–J3A5 ...................................................... Maule.

MT–7–260 & M–7–260 

MX–7–235 Star Rocket 

IO–540–W1A5 .................................................... ........................................................................... MX–7–235, MT–7–235 & M7–235 

Mod Works ....................................................... Trophy 212 Conversion 

IO–360–A3B6 ..................................................... Mooney ............................................................. 201

M–201 

Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations 54621 

Engine model Manufacturer Aircraft model 

IO–360–A1B6 ..................................................... ........................................................................... M–20–J 

IO–360–A3B6D .................................................. ........................................................................... M20J–201 

TIO–540–AF1B .................................................. ........................................................................... M20M TLS Bravo 

Moravan ........................................................... Z143L Zlin 

Z242L Zlin 

Partenavia ........................................................ P–68 Series Observer 

IO–540–K1J5 ..................................................... Piper ................................................................. 600–A Aerostar 

IO–540–S1A5 ..................................................... ........................................................................... 601–A, 601B & 601P Aerostar 

IO–540–AA1A5 .................................................. ........................................................................... 602P Sequoia 

O–540–A1B5 ...................................................... ........................................................................... PA–23–235 Aztec & PA–24–250 Comanche 

PA–23–250 Aztec 

IO–540–J4A5 ..................................................... ........................................................................... PA–23–250 Aztec 

IO–540–C1B5 .................................................... ........................................................................... PA–23–250 Aztec & PA–24–250 Comanche 

TIO–540–C1A .................................................... ........................................................................... PA–23–250T Turbo Aztec 

PA–24–150 Comanche 

O–540–A1C5 ..................................................... ........................................................................... PA–24–250 Comanche 

O–540–A1D5 ..................................................... ........................................................................... PA–24–250 Comanche 

IO–540–D4A5 .................................................... ........................................................................... PA–24–260 Comanche 

PA–24–260 Comanche 

O–540–B2C5 ..................................................... ........................................................................... PA–25–235 Pawnee 

O–540–B2B5 ...................................................... ........................................................................... PA–28–235 Cherokee 

PA–28–235 Cherokee 

IO–360–C1C6 .................................................... ........................................................................... PA–28R–201 Arrow 

IO–540–M1A5 .................................................... ........................................................................... PA–31–300 Navajo 

PA–32–260 Cherokee 6 

IO–540–K1G5 .................................................... ........................................................................... PA–32–300 & PA–32–301 Saratoga 

IO–540–K1A5 ..................................................... ........................................................................... PA–32–300 Cherokee 6 

IO–540–K1A5D .................................................. ........................................................................... PA–32–300 Cherokee 6 

IO–540–K1G5D .................................................. ........................................................................... PA–32–300R Lance 

PA–32–301R Saratoga 

IO–360–C1E6 .................................................... ........................................................................... PA–34–200 Seneca I 

IO–540–K1G5 .................................................... ........................................................................... PA–36–300 Brave 

O–360–A1H6 ..................................................... ........................................................................... PA–44–180 

LO–360–A1H6 ................................................... ........................................................................... PA–44–180 Seminole 

IO–540–K1K5 ..................................................... ........................................................................... T–35 Pillan 

Robin ................................................................ R–3000/235 

O–540–F1B5 ...................................................... Robinson .......................................................... R–44 

Rockwell ........................................................... 114 

Ruschmeyer ..................................................... MF–85 

Saab ................................................................. MFI–15 Safari or MFI–17 Supporter 

Scottish Avia .................................................... Bulldog 

Siai Marchetti ................................................... S–205 

Siai Marchetti ................................................... S–208 & SF–260 

Siai Marchetti ................................................... SF–260 

Siai Marchetti ................................................... SF–260 

Slingsby ............................................................ Firefly T3A 

Socata .............................................................. R–235 Rallye Cuerrier 

Rallye 235CA 

IO–540–C4D5D .................................................. ........................................................................... TB–20 Trinidad 

TB–200 

TIO–540–AB1AD ............................................... ........................................................................... TB–21 & TB–21–TC Trinidad TC 

IO–540–AB1A5 .................................................. Stoddard Hamilton ........................................... Glasair 

IO–540–K1H5 .................................................... Stoddard Hamilton ........................................... Glasair III

IO–540–L1C5 ..................................................... Swearingen Aircraft .......................................... SX–300 

Transava .......................................................... T–300 Skyfarmer 

AEIO–360–A1B6 ................................................ Valmet .............................................................. L–70 Vinka 

Wassmer .......................................................... WA4–21 

Yoeman ............................................................ Aviation YA–1 

Unsafe Condition 

(d) This AD results from 12 crankshaft 

failures in Lycoming model 360 and 540 

series engines rated at 300 HP or lower. We 

are issuing this AD to prevent failure of the 

crankshaft, which could result in total engine 

power loss, in-flight engine failure, and 

possible loss of the airplane. 

Compliance 

(e) You are responsible for having the 

actions required by this AD performed within 

50 hours time-in-service or 6 months after the 

effective date of this AD, whichever is earlier, 

unless the actions have already been done. 

Engines Manufactured Before March 1, 1999 

(f) If Lycoming Engines manufactured new, 

rebuilt, or overhauled your engine before 

March 1, 1999, and you haven’t had the 

crankshaft replaced, no further action is 

required. 

AEIO–540, IO–540, O–540, and TIO–540 

Series Engines Manufactured New or 

Rebuilt, Overhauled, or That Had a 

Crankshaft Installed After March 1, 1999 

(g) For AEIO–540, IO–540, O–540, and 

TIO–540 series engines manufactured new or 

rebuilt, overhauled, or that had a crankshaft 

installed after March 1, 1999, do the 

following: 

(1) If Table 1 or Table 2 of Lycoming 

Mandatory Service Bulletin (MSB) No. 566, 

dated July 11, 2005, lists your engine serial 

54622 Federal Register / Vol. 70, No. 179 / Friday, September 16, 2005 / Rules and Regulations 

number (SN), use Table 4 to verify the 

crankshaft SN. 

(2) If Table 4 of Lycoming MSB No. 566, 

dated July 11, 2005, lists your crankshaft SN, 

replace the crankshaft with a crankshaft that 

is not listed in Table 4 of Lycoming MSB No. 

566, dated July 11, 2005. 

AEIO–360, IO–360, O–360, LIO–360, and 

LO–360 Series Engines Manufactured New 

or Rebuilt, Overhauled, or That Had a 

Crankshaft Installed After March 1, 1999 

(h) For AEIO–360, IO–360, O–360, LIO–

360, and LO–360 series engines 

manufactured new or rebuilt, overhauled, or 

that had a crankshaft installed after March 1, 

1999, do the following: 

(1) If Table 3 of Lycoming MSB No. 566, 

dated July 11, 2005, lists your engine SN, use 

Table 4 to verify the crankshaft SN. 

(2) If Table 4 of Lycoming MSB No. 566, 

dated July 11, 2005, lists your crankshaft SN, 

replace the crankshaft with a crankshaft that 

is not listed in Table 4 of Lycoming MSB No. 

566, dated July 11, 2005. 

Prohibition Against Installing Certain 

Crankshafts 

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

not install any crankshaft that has a SN listed 

in Table 4 of Lycoming MSB No. 566, dated 

July 11, 2005, into any engine. 

Alternative Methods of Compliance 

(AMOCs) 

(j) The Manager, New York Aircraft 

Certification Office, has the authority to 

approve AMOCs for this AD if requested 

using the procedures found in 14 CFR 39.19. 

Related Information 

(k) None. 

Material Incorporated by Reference 

(l) You must use Lycoming Mandatory 

Service Bulletin No. 566, dated July 11, 2005, 

to perform the actions required by this AD. 

The Director of the Federal Register 

approved the incorporation by reference of 

this service bulletin in accordance with 5 

U.S.C. 552(a) and 1 CFR part 51. Contact 

Lycoming, 652 Oliver Street, Williamsport, 

PA 17701; telephone (570) 323–6181; fax 

(570) 327–7101, or on the Internet at http:// 

www.Lycoming.Textron.com for a copy of 

this service information. You may review 

copies at the Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, Room 

PL–401, Washington, DC 20590–0001, on the 

Internet at http://dms.dot.gov, or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

September 9, 2005. 

Jay J. Pardee, 

Manager, Engine and Propeller Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–18323 Filed 9–15–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22430; Directorate 

Identifier 2005–NE–34–AD; Amendment 39–

14275; AD 2005–19–10] 

RIN 2120–AA64 

Airworthiness Directives; Turbomeca 

Arrius 2 F Turboshaft Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: The FAA is adopting a new 

airworthiness directive (AD) for 

Turbomeca Arrius 2 F turboshaft 

engines. This AD requires removing 

from service certain serial number (SN) 

fuel control units (FCUs) or replacing 

the constant delta pressure diaphragm 

in those FCUs. This AD results from a 

report of an accident in July 2005 

involving a Eurocopter EC120B 

helicopter. We are issuing this AD to 

prevent an uncommanded engine inflight shutdown on a single-engine 

helicopter, resulting in a forced 

autorotation landing or an accident. 

DATES: Effective October 3, 2005. The 

Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the 

regulations as of October 3, 2005. 

We must receive any comments on 

this AD by November 15, 2005. 

ADDRESSES: Use one of the following 

addresses to comment on this AD: 

• DOT Docket Web site: Go to 

http://dms.dot.gov and follow the 

instructions for sending your comments 

electronically. 

• Government-wide rulemaking Web 

site: Go to http://www.regulations.gov 

and follow the instructions for sending 

your comments electronically. 

• Mail: Docket Management Facility; 

U.S. Department of Transportation, 400 

Seventh Street, SW., Nassif Building, 

Room PL–401, Washington, DC 20590–

0001. 

• Fax: (202) 493–2251. 

• Hand Delivery: Room PL–401 on 

the plaza level of the Nassif Building, 

400 Seventh Street, SW., Washington, 

DC, between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

Contact Turbomeca, 40220 Tarnos, 

France; telephone +33 05 59 74 40 00, 

fax +33 05 59 74 45 15, for the service 

information identified in this AD. 

FOR FURTHER INFORMATION CONTACT: 

Christopher Spinney, Aerospace 

Engineer, Engine Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803–5299; telephone 

(781) 238–7175; fax (781) 238–7199. 

SUPPLEMENTARY INFORMATION: The 

Direction Generale de L’Aviation Civile 

(DGAC), which is the airworthiness 

authority for France, notified the FAA 

that an unsafe condition may exist on 

Turbomeca Arrius 2 F turboshaft 

engines. The DGAC advises that a 

Eurocopter EC120B helicopter powered 

by an Arrius 2 F turboshaft engine 

experienced an uncommanded in-flight 

engine shutdown. An increase in fuel 

flow led to an increase in gas generator 

and power turbine speeds. Turbine 

blades separated from the disk due to 

the overspeed. Turbomeca determined 

that the fuel flow increase was caused 

by an improperly assembled and 

subsequent failure of the constant delta 

pressure (delta P) diaphragm in the 

FCU. Only certain types of constant 

delta P diaphragms have been identified 

as being capable of being improperly 

assembled. Engine serial numbers that 

may have this type of constant delta P 

diaphragm are listed in Turbomeca 

Alert Mandatory Service Bulletin (MSB) 

No. A319 73 4825, dated August 3, 

2005. The manufacturer is making spare 

FCUs available as fast as possible and 

has established a rotable pool of spares. 

After we reviewed the Turbomeca SB, 

we concluded that using the Turbomeca 

rotable pool of spares as soon as 

practicable effectively manages the risk 

of another failure of the uninspected 

engine population. To this end, we are 

requiring that FCUs identified in the 

Turbomeca SB be replaced as soon as 

practicable but not to exceed February 

28, 2006. Because the practicable 

compliance time may be quite short for 

some operators and the rotable pool 

requires consistent participation, we are 

issuing this AD as final rule; request for 

comments. 

Relevant Service Information 

We have reviewed and approved the 

technical contents of Turbomeca Alert 

MSB No. A319 73 4825, dated August 

3, 2005. That MSB lists the affected 

FCUs by SN and describes procedures 

for removing affected FCUs from service 

or replacing constant delta P 

diaphragms in those FCUs. The DGAC 

classified this service bulletin as 

mandatory and issued AD No. F–2005–

143, dated August 17, 2005, and AD No. 

F–2005–143 R1, dated August 31, 2005, 

in order to ensure the airworthiness of 

these Arrius 2 F turboshaft engines in 

France.