Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Proposed Rules 58103 

Actions Compliance Procedures 

(iii) For Model G 103 C Twin III SL sailplanes: install new P/N 103B–2360.01/2 

and P/N 103B–2360.02/2.

For sailplanes previously affected by AD 

2004–08–13: Within the next 25 hours timein-service (TIS) after June 4, 2004 (the effective date of AD 2004–08–13), unless already done. For sailplanes not previously 

affected by AD 2004–08–13: Within the 

next 25 hours time-in-service (TIS) after the 

effective date of this AD, unless already 

done.

For Models G103 TWIN ASTIR, G103 TWIN 

II, G103A TWIN II ACRO, and G103C 

TWIN III ACRO sailplanes: Follow Grob 

Service Bulletin No. MSB315–62, dated 

January 21, 2002, or Grob Service Bulletin 

No. MSB315–62/2, dated March 9, 2005. 

For Model G 103 C Twin III SL sailplanes: 

Follow Grob Service Bulletin No. MSB869–

22, dated January 22, 2002. 

(2) Do not install any CG release hook attachment bracket that is not a part number referenced in paragraphs (e)(1)(i) and (e)(1)(iii) 

of this AD, as applicable.

As of the effective date of this AD ................... Not Applicable. 

May I Request an Alternative Method of 

Compliance? 

(f) You may request a different method of 

compliance or a different compliance time 

for this AD by following the procedures in 14 

CFR 39.19. Unless FAA authorizes otherwise, 

send your request to your principal 

inspector. The principal inspector may add 

comments and will send your request to the 

Manager, Standards Office, Small Airplane 

Directorate, FAA. For information on any 

already approved alternative methods of 

compliance, contact Greg Davison, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4130; facsimile: 

(816) 329–4090. 

Is There Other Information That Relates to 

This Subject? 

(g) German AD No. 2002–066, effective 

date: March 21, 2002; and German AD No. 

2002–067, effective date: March 21, 2002, 

also address the subject of this AD. 

May I Get Copies of the Documents 

Referenced in This AD? 

(h) To get copies of the documents 

referenced in this AD, contact BURKHARDT 

GROB LUFT-UND RAUMFAHRT GmbH & 

CO KG, Letenbachstrasse 9, D–86874 

Tussenhausen-Mattsies, Germany; telephone: 

011 49 8268 998139; facsimile: 011 49 8268 

998200. To view the AD docket, go to the 

Docket Management Facility; U.S. 

Department of Transportation, 400 Seventh 

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

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

dms.dot.gov. This is docket number FAA–

2005–20803; Directorate ID 2005–CE–19–AD. 

Issued in Kansas City, Missouri, on 

September 28, 2005. 

David R. Showers, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 05–19942 Filed 10–4–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–21331; Directorate 

Identifier 2005–NE–07–AD] 

RIN 2120–AA64 

Airworthiness Directives; Engine 

Components Incorporated (ECi) 

Reciprocating Engine Connecting 

Rods 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain Lycoming Engines (formerly 

Textron Lycoming) 360 and 540 series 

reciprocating engines with ECi 

connecting rods, part number (P/N) AEL 

11750, installed. This proposed AD 

would require replacing certain serialnumbered connecting rods, P/N AEL 

11750. This proposed AD would also 

prohibit installing certain ECi 

connecting rods, P/N AEL 11750 into 

any Lycoming 360 or 540 series 

reciprocating engines. This proposed 

AD results from reports of connecting 

rods with excessive variation in 

circularity of the journal bores. We are 

proposing this AD to prevent fatigue 

failure of the connecting rod and 

uncommanded shutdown of the engine. 

DATES: We must receive any comments 

on this proposed AD by December 5, 

2005. 

ADDRESSES: Use one of the following 

addresses to comment on this proposed 

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. 

You may examine the comments on 

this proposed AD in the AD docket on 

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

FOR FURTHER INFORMATION CONTACT: 

Peter Hakala, Aerospace Engineer, 

Special Certification Office, FAA, 

Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, TX 76193; telephone 

(817) 222–5145; fax (817) 222–5785. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send us any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–21331; Directorate Identifier 

2005–NE–07–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:// 

dms.dot.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 DOT 

docket Web site, anyone can find and 

read the comments in any of our 

dockets, including the name of the 

individual who sent the comment (or 

58104 Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Proposed Rules 

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) or you may visit 

http://dms.dot.gov. 

Examining the AD Docket 

You may examine the docket that 

contains the proposal, 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 

Docket Management Facility receives 

them. 

Discussion 

On October 16, 2003, ECi informed 

the FAA that an engine experienced an 

in-flight engine failure and 

uncommanded shutdown. The failure 

occurred after 50 hours time-in-service 

(TIS) after an engine overhaul. The 

engine overhaul included replacing the 

engine crankshaft, the connecting rods, 

and the connecting rod bearings. We 

conducted a post-accident investigation 

that included an engine teardown. The 

engine teardown showed that one 

connecting rod and one connecting rod 

bearing were destroyed. The three 

remaining connecting rod bearings had 

an unusual ‘‘tank tread’’ pattern around 

the surface that mates with the 

crankshaft journal. A visual 

examination of the three remaining 

connecting rods revealed the journal 

bores had the same ‘‘tank tread’’ pattern 

found on the mating surface of the 

bearings. 

Results of the FAA’s Investigation of 

New Connecting Rods 

We approved reciprocating engine 

connecting rods, P/N AEL 11750, for use 

on Lycoming 360 and 540 series 

reciprocating engines under a Parts 

Manufacturer Approval (PMA). The 

Airmotive Engineering Corp, Division of 

Engine Components Incorporated, holds 

the PMA. ECi markets the parts as ECi 

parts. We determined the ECi 

engineering drawings for the connecting 

rods contain inadequate criteria to 

control circularity of the bearing bore. 

Because of that, the manufacturing 

process used to machine the bore 

resulted in excessive scalloping. The 

scalloping resulted in excessive 

variation in the circularity necessary for 

the proper functioning of the connecting 

rods. We also determined the inspection 

methods that ECi used to inspect the 

newly manufactured connecting rods 

were not sufficiently accurate to identify 

the manufacturing defects in circularity. 

We obtained four new ECi connecting 

rods from the field and two new ECi 

connecting rods directly from ECi. A 

U.S. Government test facility measured 

the connecting rods using highprecision test measuring equipment. 

The test facility found the journal bores 

in all of the connecting rods had 

excessive scalloping. Our analysis of 

measurements from the test facility 

show that the scalloping prevents 

proper fitting between the connecting 

rod and it’s associated rod bearing. The 

poor fit between these critical engine 

components results in a significant 

reduction in performance and fatigue 

strength. Journal bores with excessive 

surface scalloping or machine chattering 

can result in two adverse conditions: 

(1) Poor contact between the journal 

bore and it’s bearing substantially 

reduces heat transfer from the bearing. 

The resulting increase in bearing 

temperature substantially reduces the 

fatigue strength of the bearing. 

(2) The scalloping or machine 

chattering prevents adequate 

development of the hydrodynamic oil 

film needed to lubricate and cool the 

bearing. This allows metal-to-metal 

contact between the bearing and the 

connecting rod journal 

On December 22, 2003, ECi made a 

design drawing revision to better define 

dimensions and improve the quality 

control for the manufacture of the 

connecting rod, P/N AEL 11750. We 

have not received any reports of service 

difficulties for connecting rods, P/N 

AEL 11750, produced after January 2004 

with the improved design. 

This condition, if not corrected, could 

result in fatigue failure of the 

connecting rod and uncommanded 

shutdown of the engine. 

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. We are proposing this AD, 

which would require: 

• Replacing certain serial-numbered 

ECi connecting rods, P/N AEL 11750, 

with 1,500 or more hours TIS on the 

connecting rod, within 50 hours TIS 

after the effective date of the AD. 

• Replacing certain serial-numbered 

ECi connecting rods, P/N AEL 11750, 

with fewer than 1,500 hours TIS on the 

connecting rod, before accumulating 

1,500 hours TIS on the connecting rod. 

This proposed AD would also 

prohibit installing any ECi connecting 

rod, P/N AEL 11750, with a serial 

number 54/6 or lower, into any engine 

after the effective date of the AD. 

Costs of Compliance 

We estimate that this proposed AD 

would affect about 2,800 Lycoming 

Engines 360 and 540 series 

reciprocating engines installed on 

aircraft of U.S. registry. We also estimate 

that it would take about 4 work hours 

per engine to perform the proposed 

actions, and that the average labor rate 

is $65 per work hour. Required parts 

would cost about $450 per connecting 

rod. Based on these figures, we estimate 

the total cost of the proposed AD to U.S. 

operators to be $1,988,000. ECi has 

indicated that they might provide 

operators and repair stations credit for 

returned connecting rods. 

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 regulation: 

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 

Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Proposed Rules 58105 

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 adding 

the following new airworthiness 

directive: 

Engine Components Incorporated (ECi): 

Docket No. FAA–2005–21331; 

Directorate Identifier 2005–NE–07–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

December 5, 2005. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Lycoming Engines 

(formerly Textron Lycoming) 360 and 540 

series reciprocating engines specified in 

Table 1 of this AD with Engine Components 

Incorporated (ECi) connecting rods, part 

number (P/N) AEL 11750 installed. 

TABLE 1.—ENGINE MODELS

Engine Model 

0–360– A1A, A1AD, A1C, A1D, A1F, A1F6, 

A1F6D, A1G, A1G6, A1G6D, A1H, A1H6, 

A1LD, A1P, A2A, A2D, A2E, A2F, A2G, 

A2H, A3A, A3AD, A3D, A4A, A4AD, A4D, 

A4G, A4J, A4K, A4M, A4N, A4P, A5AD, 

B1A, B1B, B2A, B2B, C1A, C1C, C1E, 

C1F, C1G, C2A, C2B, C2C, C2D, C2E, 

C4F, C4P, D1A, D2A, D2B, F1A6, G1A6, 

J2A; 

HO–360– A1A, B1A, B1B, C1A; 

TABLE 1.—ENGINE MODELS—

Continued 

IO–360– B1A, B1B, B1C, B1D, B1E, B1F, 

B1F6, B1G6, B2E, B2F, B2F6, B4A, E1A, 

F1A, L2A; 

LO–360– A1G6D, A1H6; 

HIO–360– A1A, A1B, B1A, B1B; 

AEIO–360– B1B, B1D, B1F, B1F6, B1G6, 

B2F, B2F6, B4A, H1A, H1B; 

O–540– A1A, A1A5, A1B5, A1C5, A1D, 

A1D5, A2B, A3D5, A4A5, A4B5, A4C5, 

A4D5, B1A5, B1B5, B1D5, B2A5, B2B5, 

B2C5, B4A5, B4B5, D1A5, E4A5, E4B5, 

E4C5, F1A5, F1B5, G1A5, G2A5, H1A5, 

H1A5D, H1B5D, H2A5, H2A5D, H2B5D; 

AEIO–540– D4A5, D4B5, D4C5, D4D5; 

IO–540– A1A5, B1A5, B1B5, B1C5, C1B5, 

C1C5, C2C, C4B5, C4C5, C4D5, C4D5D, 

D4A5, D4B5, D4C5, E1A5, E1B5, E1C5, 

G1A5, G1B5, G1C5, G1D5, G1E5, G1F5, 

J4A5, N1A5, P1A5, R1A5, T4A5D, T4B5, 

T4B5D, T4C5D, V4A5, V4A5D; 

LTIO–540– K1AD; 

TIO–540– C1A, E1A, G1A, H1A, K1AD, 

AA1AD, AB1AD, AB1BD, AF1A, AF1B, 

AG1A. 

These engines are installed on, but not 

limited to, the aircraft listed in Table 2 of this 

AD. 

TABLE 2.—AIRCRAFT MODELS

Aircraft manufacturer Aircraft model 

Aero Boero ............................................................................................... AB–180, AB–260. 

Aero Commander ..................................................................................... Lark (100), Aero Commander (500, 500–B, 500–E, 500–U). 

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

Aerofab Inc. .............................................................................................. Renegade 250, Turbo Renegade (270). 

Aviamilano ................................................................................................ Flamingo (F–250). 

Aviat .......................................................................................................... Husky. 

Avions Pierre Robin .................................................................................. (HR100/250). 

Beagle ....................................................................................................... Airedale (A–109), Husky (D5–180 01–U). 

Beech Aircraft ........................................................................................... Travel-Air (95, B–95, B–95A, B–95B), Duchess 76, Sport, Musketeer 

Custom III, Sundowner 180. 

Bellanca Aircraft ....................................................................................... Scout (8GCBC–CS, 8GCBC FP), Super Decathlon (8KCAB–180), 

Aries T–250. 

Bolkow ...................................................................................................... 207, Klemm (K1–107C). 

Britten-Norman ......................................................................................... BN–2. 

Brooklanda ................................................................................................ Scoutmaster. 

C.A.A.R.P. ................................................................................................ S A.N. (M–23III), C.A.P. (10). 

C. Itoh and Co. ......................................................................................... Fuji FA–200. 

Center Est Aeronautique .......................................................................... Regente (DR–253). 

Cerva ........................................................................................................ (CE–43 Guepard). 

Cessna Aircraft ......................................................................................... Cardinal, Cardinal 172, Teal III. TSC (1A3), Skyhawk, Cutlass RG. 

Christen .................................................................................................... Husky (A–1), Christen. Pitts (S–2S), (S–2B). 

DeHavilland .............................................................................................. Drover (DHA–3MK3), Heron Conversion. 

Dinfia ......................................................................................................... Ranquel (lA–51), Querandi (1A–45). 

Dornier ...................................................................................................... (DO–28 , DO–28–B1, DO–8–B1). 

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

Doyn Aircraft ............................................................................................. Doyn-Beech (Beech 95). 

Doyn Aircraft ............................................................................................. Doyn-Piper (PA–23 ‘‘160’’, PA–23 ‘‘200’’, PA–24 ‘‘250’’, PA–23 ‘‘250’’). 

Earl Horton ............................................................................................... Pawnee (Piper PA–25). 

Embraer .................................................................................................... Corioca (EMB–710), Impanema ‘‘AG.’’

F.F.A. ........................................................................................................ Bravo (200). 

Found Bros. .............................................................................................. (FBA–2C), Centennial (100). 

Fuji ............................................................................................................ (FA–200). 

General Aviation ....................................................................................... Model 114. 

Gippsland .................................................................................................. GA–200. 

Great Lakes .............................................................................................. Trainer. 

Grob .......................................................................................................... G115/Sport-Acro. 

Grumman American ................................................................................. Tiger. 

58106 Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Proposed Rules 

TABLE 2.—AIRCRAFT MODELS—Continued 

Aircraft manufacturer Aircraft model 

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

Hughes Tool Co. ...................................................................................... (269A, 269–A–1, YHO–2HU, 300). 

Intermountain Mfg. Co. ............................................................................. Call Air (A–6, A–9, IAR821, IAR–822, IAR–826, IAR–823). 

Kingsford-Smith ........................................................................................ Bushmaster (O–6). 

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

Malmo ....................................................................................................... Vipan (MF–10B, MF1–10). 

Maule ........................................................................................................ Star Rocket MX–7–180, MX–7–180A, Star Rocket (MX–7–235), Super 

Rocket (M–6–235), Super Std. Rocket (M–7–235). 

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

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

Statesman (M–20G), Mark ‘‘21’’ (M–20E), .’’TLS’’ M20M. 

Moravan .................................................................................................... Zlin-50L. 

Mundry ...................................................................................................... CAP–10. 

Nash Aircraft Ltd. ...................................................................................... Petrel. 

Neiva ......................................................................................................... lPD–590V. 

Norman Aeroplace Co. ............................................................................. NAC–1 Freelance. 

Omega Aircraft ......................................................................................... BS–12D1. 

Partenavia ................................................................................................. Oscar (P–66). 

Penn Yan .................................................................................................. Super Cub Conversion.

Pilatus Britten-Norman ............................................................................. Islander (BN–2A–26), Islander (BN–2A–27, IslanderII (BN–2B–26), Islander (BN–2A–21), Trislander (BN–2A–Mark III–2). 

Piper Aircraft ............................................................................................. Comanche (PA–24), Seminole (PA–44), Cherokee ‘‘C’’(PA–28 ‘‘180’’), 

Cherokee ‘‘D’’ (PA–28 ‘‘180’’), Archer II(PA–28 ‘‘18’’), Arrow (PA–28 

‘‘180R’’), Seminole (PA–44), Comanche (PA–24 ‘‘150’’), Aztec (PA–

23 ‘‘250’’),Cherokee (PA–24 ‘‘250’’), Pawnee (PA–24 

‘‘235’’),Cherokee (PA–28 ‘‘235’’), Aztec (PA–23 ‘‘235’’),Cherokee 

(PA–28 ‘‘235’’), Comanche (PA–24 ‘‘260’’),Cherokee Six (PA–32 

‘‘260’’), Pawnee (PA–25 ‘‘260’’),Aztec B (PA–23 ‘‘250’’), Comanche 

(PA–24 ‘‘250’’),Aztec C (PA–23 ‘‘250’’), Aztec F, Comanche (PA–

24),Turbo Aztec (PA–23–250). 

Pitts ........................................................................................................... S–1S. 

Poeschel ................................................................................................... P–300. 

Procaer ..................................................................................................... Picchio (F–15–A). 

Rawdon Brow ........................................................................................... Radon (T–1). 

Regente .................................................................................................... N–591. 

Rhein-Flugzeughau .................................................................................. RF–V 

Riley Aircraft ............................................................................................. Rocket-Cessna (310), Turbo-Rocket, Turbo-Aztec. 

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

1180T). 

Robinson ................................................................................................... R–44. 

Rockwell ................................................................................................... Commander (114, 114B, 114TC). 

S A.A.B. .................................................................................................... Safir (91–D). 

Schweizer Aircraft Corporation ................................................................. 269A. 

S.O.C.A.T.A. ............................................................................................. Tobago (TB–10), Rallye Commodore (MS–893), Rallye 180GI, 

Sportana Sportsman (RS–180), Rallye 235CA,Rallye 235GT, Rallye 

235C, TB–20, Trinidad TB–20,Trinidad TC TB–21. 

Shrike ........................................................................................................ (500–S). 

Societe Aeronautique Normande .............................................................

Mousquetaire 

D–140, Jodel (D–140C). 

Siai-Marchetti ............................................................................................

Silvercraft 

Std. Helicopter 

(S–205, SF–260, SF–208). 

Sud ........................................................................................................... Gardan (GY–180). 

T. R. Smith Aircraft ................................................................................... Aerostar, (600). 

United Consultants ................................................................................... See-Bee. 

Utva .......................................................................................................... 75. 

Valmet ....................................................................................................... PIK–23. 

Varga ........................................................................................................ Kachina. 

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

40), (WA–50), Europa WA–52, WA–421, WA4–2V. 

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

Unsafe Condition 

(d) This AD results from reports of 

connecting rods with excessive variation in 

circularity of the journal bores. We are 

issuing this AD to prevent fatigue failure of 

the connecting rod and uncommanded 

shutdown of the engine. 

Compliance 

(e) 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 Not Repaired or Overhauled Since 

New 

(f) If your engine has not been overhauled 

or had any repair since new, no further 

action is required. 

Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Proposed Rules 58107 

Engines Overhauled or Repaired Since New 

(g) If your engine was overhauled or 

repaired 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 connecting rods, P/N AEL 11750. 

(2) If the connecting rods are not ECi, 

P/N AEL 11750, no further action is required. 

(3) If the connecting rods are ECi, P/N AEL 

11750, and if the serial number is 54/7 or 

higher, no further action is required. 

(4) If the connecting rods are ECi, P/N AEL 

11750, and if the serial number is 54/6 or 

lower, do the following: 

(i) If the connecting rod has 1,500 or more 

hours time-in-service (TIS), replace the 

connecting rod with a connecting rod that 

has a SN 54/7 or higher, or that has a P/N 

not specified in this AD within 50 hours TIS 

after the effective date of this AD. 

(ii) If the connecting rod has fewer than 

1,500 hours TIS, replace the connecting rod 

with a connecting rod that has a SN 54/7 or 

higher, or that has a P/N not specified in this 

AD before accumulating 1,500 hours TIS on 

the connecting rod. 

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

not install any ECi connecting rod, P/N AEL 

11750, that has SN 54/6 or lower into any 

engine. 

Alternative Methods of Compliance 

(AMOCs) 

(i) The Manager, Special Certification 

Office, has the authority to approve 

alternative methods of compliance for this 

AD if requested using the procedures found 

in 14 CFR 39.19. 

Related Information 

(j) None. 

Issued in Burlington, Massachusetts, on 

September 28, 2005. 

Francis A. Favara, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 05–19940 Filed 10–4–05; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–22206; Directorate 

Identifier 2005–CE–45–AD] 

RIN 2120–AA64 

Airworthiness Directives; DG 

Flugzeugbau GmbH Models DG–800B 

and DG–500MB Sailplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to adopt a 

new airworthiness directive (AD) for 

certain DG Flugzeugbau GmbH Models 

DG–800B and DG–500MB sailplanes. 

This proposed AD would require you to 

modify the connection of the starter ring 

gear to the lower drive belt pulley 

adapter. This proposed AD results from 

mandatory continuing airworthiness 

information (MCAI) issued by the 

airworthiness authority for Germany. 

We are issuing this proposed AD to 

prevent the bolts currently used to 

connect the starter ring gear to the drive 

belt pulley adapter from shearing off 

and the bolt heads falling into the 

engine compartment. Failure of this 

connection could render the engine 

inoperative. Consequently, this failure 

could lead to loss of control of the 

sailplane. 

DATES: We must receive any comments 

on this proposed AD by November 9, 

2005. 

ADDRESSES: Use one of the following to 

submit comments on this proposed 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–

001. 

• Fax: 1–202–493–2251. 

• 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. 

To get the service information 

identified in this proposed AD, contact 

DG–Flugzeugbau, Postbox 41 20, D–

76625 Bruchsal, Federal Republic of 

Germany; telephone: ++49 7257 890; 

facsimile: ++45 7257 8922; e-mail: 

www.dg-flugzeugbau.de. 

To view the comments to this 

proposed AD, go to http://dms.dot.gov. 

This is docket number FAA–2005–

22206; Directorate Identifier 2005–CE–

45–AD. 

FOR FURTHER INFORMATION CONTACT: 

Gregory Davison, Glider Project 

Manager, ACE–112, Small Airplane 

Directorate, 901 Locust, Room 301, 

Kansas City, Missouri 64106; telephone: 

(816) 329–4130; facsimile: (816) 329–

4090. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

How do I comment on this proposed 

AD? We invite you to submit any 

written relevant data, views, or 

arguments regarding this proposal. Send 

your comments to an address listed 

under ADDRESSES. Include the docket 

number, ‘‘FAA–2005–22206; Directorate 

Identifier 2005–CE–45–AD’’ at the 

beginning of your comments. We will 

post all comments we receive, without 

change, to http://dms.dot.gov, including 

any personal information you provide. 

We will also post a report summarizing 

each substantive verbal contact with 

FAA personnel concerning this 

proposed rulemaking. Using the search 

function of our docket Web site, anyone 

can find and read the comments 

received into any of our dockets, 

including the name of the individual 

who sent the comment (or signed the 

comment on behalf of an association, 

business, labor union, etc.). This is 

docket number FAA–2005–22206; 

Directorate Identifier 2005–CE–45–AD. 

You may review the DOT’s complete 

Privacy Act Statement in the Federal 

Register published on April 11, 2000 

(65 FR 19477–78) or you may visit 

http://dms.dot.gov. 

Are there any specific portions of this 

proposed AD I should pay attention to? 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this proposed AD. If you contact us 

through a nonwritten communication 

and that contact relates to a substantive 

part of this proposed AD, we will 

summarize the contact and place the 

summary in the docket. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD in light of those comments 

and contacts. 

Docket Information 

Where can I go to view the docket 

information? You may view the AD 

docket that contains the proposal, any 

comments received, and any final 

disposition in person at the DMS Docket 

Offices between 9 a.m. and 5 p.m. 

(eastern time), Monday through Friday, 

except Federal holidays. The Docket 

Office (telephone 1–800–647–5227) is 

located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. You may also view the AD 

docket on the Internet at http:// 

dms.dot.gov. The comments will be 

available in the AD docket shortly after 

the DMS receives them. 

Discussion 

What events have caused this 

proposed AD? The Luftfahrt-Bundesamt 

(LBA), which is the airworthiness 

authority for Germany, recently notified 

FAA that an unsafe condition may exist 

on certain DG Flugzeugbau GmbH