Airworthiness Directives; Engine Components Incorporated (ECi) Reciprocating Engine Connecting Rods, 58103-58107 [05-19940]
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Actions
Compliance
(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.
(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.
Procedures
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.
As of the effective date of this AD ...................
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.
Not Applicable.
May I Request an Alternative Method of
Compliance?
DEPARTMENT OF TRANSPORTATION
(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.
Federal Aviation Administration
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 https://
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]
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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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
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 https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://www.regulations.gov
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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 https://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 https://
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
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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
https://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
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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
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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
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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:
58105
Engine Components Incorporated (ECi):
Docket No. FAA–2005–21331;
Directorate Identifier 2005–NE–07–AD.
TABLE 1.—ENGINE MODELS—
Continued
Comments Due Date
(a) The Federal Aviation Administration
(FAA) must receive comments on this
airworthiness directive (AD) action by
December 5, 2005.
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.
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;
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 ...............................................................................................
Aero Commander .....................................................................................
Aero Engine Service Ltd. .........................................................................
Aerofab Inc. ..............................................................................................
Aviamilano ................................................................................................
Aviat ..........................................................................................................
Avions Pierre Robin ..................................................................................
Beagle .......................................................................................................
Beech Aircraft ...........................................................................................
AB–180, AB–260.
Lark (100), Aero Commander (500, 500–B, 500–E, 500–U).
Victa (R–2).
Renegade 250, Turbo Renegade (270).
Flamingo (F–250).
Husky.
(HR100/250).
Airedale (A–109), Husky (D5–180 01–U).
Travel-Air (95, B–95, B–95A, B–95B), Duchess 76, Sport, Musketeer
Custom III, Sundowner 180.
Scout (8GCBC–CS, 8GCBC FP), Super Decathlon (8KCAB–180),
Aries T–250.
207, Klemm (K1–107C).
BN–2.
Scoutmaster.
S A.N. (M–23III), C.A.P. (10).
Fuji FA–200.
Regente (DR–253).
(CE–43 Guepard).
Cardinal, Cardinal 172, Teal III. TSC (1A3), Skyhawk, Cutlass RG.
Husky (A–1), Christen. Pitts (S–2S), (S–2B).
Drover (DHA–3MK3), Heron Conversion.
Ranquel (lA–51), Querandi (1A–45).
(DO–28 , DO–28–B1, DO–8–B1).
Doyn-Cessna (170B, 172, 172A, 172B).
Doyn-Beech (Beech 95).
Doyn-Piper (PA–23 ‘‘160’’, PA–23 ‘‘200’’, PA–24 ‘‘250’’, PA–23 ‘‘250’’).
Pawnee (Piper PA–25).
Corioca (EMB–710), Impanema ‘‘AG.’’
Bravo (200).
(FBA–2C), Centennial (100).
(FA–200).
Model 114.
GA–200.
Trainer.
G115/Sport-Acro.
Tiger.
Bellanca Aircraft .......................................................................................
Bolkow ......................................................................................................
Britten-Norman .........................................................................................
Brooklanda ................................................................................................
C.A.A.R.P. ................................................................................................
C. Itoh and Co. .........................................................................................
Center Est Aeronautique ..........................................................................
Cerva ........................................................................................................
Cessna Aircraft .........................................................................................
Christen ....................................................................................................
DeHavilland ..............................................................................................
Dinfia .........................................................................................................
Dornier ......................................................................................................
Doyn Aircraft .............................................................................................
Doyn Aircraft .............................................................................................
Doyn Aircraft .............................................................................................
Earl Horton ...............................................................................................
Embraer ....................................................................................................
F.F.A. ........................................................................................................
Found Bros. ..............................................................................................
Fuji ............................................................................................................
General Aviation .......................................................................................
Gippsland ..................................................................................................
Great Lakes ..............................................................................................
Grob ..........................................................................................................
Grumman American .................................................................................
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TABLE 2.—AIRCRAFT MODELS—Continued
Aircraft manufacturer
Aircraft model
H.A.L. ........................................................................................................
Hughes Tool Co. ......................................................................................
Intermountain Mfg. Co. .............................................................................
Kingsford-Smith ........................................................................................
Lake Aircraft .............................................................................................
Malmo .......................................................................................................
Maule ........................................................................................................
HPT–32.
(269A, 269–A–1, YHO–2HU, 300).
Call Air (A–6, A–9, IAR821, IAR–822, IAR–826, IAR–823).
Bushmaster (O–6).
Colonial (C–2, LA–4, 4A or 4P), Seawolf.
Vipan (MF–10B, MF1–10).
Star Rocket MX–7–180, MX–7–180A, Star Rocket (MX–7–235), Super
Rocket (M–6–235), Super Std. Rocket (M–7–235).
Twin Courier (H–500), (U–5).
Master ‘‘21’’ (M–20D, M–20E), Mark ‘‘20B’’, ‘‘20D’’,(M20B, M20C),
Statesman (M–20G), Mark ‘‘21’’ (M–20E), .’’TLS’’ M20M.
Zlin-50L.
CAP–10.
Petrel.
lPD–590V.
NAC–1 Freelance.
BS–12D1.
Oscar (P–66).
Super Cub Conversion.
Islander (BN–2A–26), Islander (BN–2A–27, IslanderII (BN–2B–26), Islander (BN–2A–21), Trislander (BN–2A–Mark III–2).
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).
S–1S.
P–300.
Picchio (F–15–A).
Radon (T–1).
N–591.
RF–V
Rocket-Cessna (310), Turbo-Rocket, Turbo-Aztec.
Regent (DR400/180), Remorqueur (DR400/180R), R–3170, Aiglon (R–
1180T).
R–44.
Commander (114, 114B, 114TC).
Safir (91–D).
269A.
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.
(500–S).
D–140, Jodel (D–140C).
Mid-States Mfg. Co. ..................................................................................
Mooney Aircraft ........................................................................................
Moravan ....................................................................................................
Mundry ......................................................................................................
Nash Aircraft Ltd. ......................................................................................
Neiva .........................................................................................................
Norman Aeroplace Co. .............................................................................
Omega Aircraft .........................................................................................
Partenavia .................................................................................................
Penn Yan ..................................................................................................
Pilatus Britten-Norman .............................................................................
Piper Aircraft .............................................................................................
Pitts ...........................................................................................................
Poeschel ...................................................................................................
Procaer .....................................................................................................
Rawdon Brow ...........................................................................................
Regente ....................................................................................................
Rhein-Flugzeughau ..................................................................................
Riley Aircraft .............................................................................................
Robin ........................................................................................................
Robinson ...................................................................................................
Rockwell ...................................................................................................
S A.A.B. ....................................................................................................
Schweizer Aircraft Corporation .................................................................
S.O.C.A.T.A. .............................................................................................
Shrike ........................................................................................................
Societe Aeronautique Normande .............................................................
Mousquetaire
Siai-Marchetti ............................................................................................
Silvercraft
Std. Helicopter
Sud ...........................................................................................................
T. R. Smith Aircraft ...................................................................................
United Consultants ...................................................................................
Utva ..........................................................................................................
Valmet .......................................................................................................
Varga ........................................................................................................
Wassmer ...................................................................................................
Yoeman Aviation ......................................................................................
(S–205, SF–260, SF–208).
Gardan (GY–180).
Aerostar, (600).
See-Bee.
75.
PIK–23.
Kachina.
Super 4 (WA–50A), Sancy (WA–40), Baladou (WA–40), Pariou (WA–
40), (WA–50), Europa WA–52, WA–421, WA4–2V.
YA–1.
Unsafe Condition
Compliance
(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.
(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.
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Federal Register / Vol. 70, No. 192 / Wednesday, October 5, 2005 / Proposed Rules
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
The FAA proposes to adopt a
new airworthiness directive (AD) for
certain DG Flugzeugbau GmbH Models
SUMMARY:
VerDate Aug<31>2005
17:08 Oct 04, 2005
Jkt 208001
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.
We must receive any comments
on this proposed AD by November 9,
2005.
DATES:
Use one of the following to
submit comments on this proposed AD:
• DOT Docket web site: Go to https://
dms.dot.gov and follow the instructions
for sending your comments
electronically.
• Government-wide rulemaking Web
site: Go to https://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 https://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.
ADDRESSES:
SUPPLEMENTARY INFORMATION:
Comments Invited
How do I comment on this proposed
AD? We invite you to submit any
written relevant data, views, or
PO 00000
Frm 00024
Fmt 4702
Sfmt 4702
58107
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 https://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
https://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 https://
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
E:\FR\FM\05OCP1.SGM
05OCP1
]]>Agencies
[Federal Register Volume 70, Number 192 (Wednesday, October 5, 2005)]
[Proposed Rules]
[Pages 58103-58107]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 05-19940]
-----------------------------------------------------------------------
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 serial-numbered 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 https://dms.dot.gov and follow
the instructions for sending your comments electronically.
Government-wide rulemaking Web site: Go to https://
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 https://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 https://
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
[[Page 58104]]
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 https://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 high-precision 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
[[Page 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.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 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;
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.
[[Page 58106]]
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.......... D-140, Jodel (D-140C).
Mousquetaire...........................
Siai-Marchetti......................... (S-205, SF-260, SF-208).
Silvercraft............................
Std. Helicopter........................
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.
[[Page 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
