Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules 74873 

Field name FDIC field description Questions/comments for the 

industry 

11 ......... CS_Suffix ....................... Customer Suffix: The suffix of the individual/ personal customer—i.e. 

Jr., Sr., III, etc. 

12 ......... CS_Comp_Name ........... Customer Company Name: The company name of the business customer.How are business customers reflected in your customer 

records? Are there multiple 

name/address fields? 

13 ......... CS_Address_1 ............... Address Line 1: Two lines (Fields 13 & 14) are provided to enter the 

street, PO Box, suite number, etc. of the address. 

14 ......... CS_Address_2 ............... Address Line 2: Additional address field. 

15 ......... CS_City .......................... City: Enter the city associated with the mailing address of the customer. 

16 ......... CS_State ........................ State: Enter the state abbreviation associated with the mailing address of the customer. 

17 ......... CS_ZIP ........................... ZIP: This field allows for the ZIP+ 4 Code associated with the mailing address of the customer. 

18 ......... CS_Country .................... Country: This field should identify the country associated with the 

mailing address. Provide the name of the country or the standard 

country code. 

19 ......... CS_Birth_Dt ................... Customer Birth Date: The birth date on record for the customer. 

Must be entered in MMDDYYYY format. 

20 ......... CS_Telephone ............... Customer Telephone Number: The telephone number on record for 

the customer. 

21 ......... CS_Email ....................... Customer Email Address: The e-mail address on record for the customer. 

* * * * * 

By order of the Board of Directors. 

Dated at Washington, DC, this 5th day of 

December, 2006. 

Federal Deposit Insurance Corporation. 

Robert E. Feldman, 

Executive Secretary. 

[FR Doc. E6–21143 Filed 12–12–06; 8:45 am] 

BILLING CODE 6714–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2006–23871; Directorate 

Identifier 2006–NE–01–AD] 

RIN 2120–AA64 

Airworthiness Directives; General 

Electric Company (GE) CF6–80C2 

Turbofan Engines 

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 GE 

CF6–80C2 series turbofan engines. This 

proposed AD would require replacing 

certain installed part number (P/N) and 

serial number (SN) cast titanium weldrepaired forward engine mount 

platforms and cast titanium forward 

mount yokes, with a forged titanium or 

a non-welded cast titanium part. This 

proposed AD results from the discovery 

of cracks, in a weld-repaired area on a 

forward engine mount platform and a 

forward engine mount yoke, found 

during a fluorescent penetrant 

inspection (FPI). These parts were weldrepaired during manufacture. We are 

proposing this AD to prevent cracks in 

the forward engine mount platform and 

forward engine mount yoke that could 

result in possible separation of the 

engine from the airplane. 

DATES: We must receive any comments 

on this proposed AD by January 12, 

2007. 

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: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; telephone (781) 238–7176; fax 

(781) 238–7199. 

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–

2006–23871; Directorate Identifier 

2006–NE–01–AD’’ in the subject line of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of the proposed AD. We will 

consider all comments received by the 

closing date and may amend the 

proposed AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

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 

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 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. 


jlentini on PROD1PC65 with PROPOSAL
74874 Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules 

Examining the AD Docket 

You may examine the docket that 

contains the proposal, any comments 

received, and any final disposition in 

person at the DOT Docket Office 

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 

During an FPI inspection of the 

forward engine mount platform and 

forward engine mount yoke, an air 

carrier found crack indications in the 

forward engine mount platform and 

yoke, and reported the findings to GE. 

An audit of GE’s manufacturing records 

revealed 25 cast titanium forward 

engine mount platforms, including the 

one found cracked, and 59 cast titanium 

forward engine mount yokes, had been 

weld-repaired at manufacture in either 

the pylon thrust pin hole or in the pylon 

attach bolt-hole region. Therefore, 25 

cast titanium forward engine mount 

platforms and 59 cast titanium forward 

engine mount yokes would be affected 

by this proposed AD. Although the weld 

repairs were an approved GE practice at 

the time, it has since been determined 

that the welding results in cracking in 

critical areas of the forward engine 

mount platforms and yokes. This 

condition, if not corrected, could result 

in possible separation of the engine 

from the airplane. 

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 

installed P/N and SN cast titanium 

weld-repaired forward engine mount 

platforms and cast titanium forward 

mount yokes with a forged titanium or 

a non-welded cast titanium part. 

Costs of Compliance 

There are 25 engines in service that 

contain the substandard forward engine 

mount platforms and 59 engines in 

service that contain the substandard 

forward engine mount yokes. We 

estimate that this proposed AD would 

affect 84 CF6–80C2 engines installed on 

airplanes of U.S. registry. We estimate 

that it would take 34 work-hours per 

engine to replace the weld-repaired cast 

titanium forward engine mount 

platforms and the weld-repaired cast 

titanium forward engine mount yokes. 

The average labor rate is $80 per workhour. Required forward engine mount 

parts would cost about $12,168 per 

engine. Required forward engine mount 

yoke parts would cost about $39,560 per 

engine. Based on these figures, we 

estimate the total cost of the proposed 

AD to U.S. operators to be $2,866,720. 

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 

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: 

General Electric Company: Docket No. FAA–

2006–23871; Directorate Identifier 2006–

NE–01–AD. 

Comments Due Date 

(a) The Federal Aviation Administration 

(FAA) must receive comments on this 

airworthiness directive (AD) action by 

January 12, 2007. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following 

General Electric Company (GE) turbofan 

engines with cast titanium assembly engine 

mount platforms part numbers (P/Ns) 

1292M13G06, 1301M28G08, 1459M70G07, 

and 1846M24G04 and cast titanium assembly 

engine mount yokes P/Ns 9383M43G14 and 

9383M43G16 installed. 

CF6–80C2A1 ................................. CF6–80C2A8 ................................ CF6–80C2B4 ................................ CF6–80C2B4F 

CF6–80C2A2 ................................. CF6–80C2A5F .............................. CF6–80C2B6 ................................ CF6–80C2B5F 

CF6–80C2A3 ................................. CF6–80C2B1 ................................ CF6–80C2B1F .............................. CF6–80C2B6F 

CF6–80C2A5 ................................. CF6–80C2B2 ................................ CF6–80C2B2F .............................. CF6–80C2B6FA 


jlentini on PROD1PC65 with PROPOSAL
Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules 74875 

These engines are installed on, but not 

limited to, Boeing 747, Boeing 767, and 

Airbus A300–600 airplanes. 

Unsafe Condition 

(d) This AD results from the discovery of 

cracks in a forward engine mount platform 

and a forward engine mount yoke found 

during fluorescent penetrant inspection (FPI). 

We are issuing this AD to prevent cracks in 

the forward engine mount platform and 

forward engine mount yoke that could result 

in possible separation of the engine from the 

airplane. 

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. 

P/N and SN Weld-Repaired Forward Engine 

Mount Platforms and Forward Engine Mount 

Yokes Requiring Replacement 

(f) Table 1 of this AD lists the P/Ns and 

serial numbers (SNs) of the weld-repaired 

forward engine mount platforms that have a 

weld repair in a non-redundant area of the 

mount and must be replaced. 

TABLE 1.—WELD-REPAIRED FORWARD

ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE

A WELD REPAIR IN A NON-REDUNDANT AREA OF THE MOUNT. 

P/Ns SNs 

1292M13G06 or 1846M24G04 WACHH228 

WACHH254 

WACHH285 

WACHH290 

WACHH292 

WACHH295 

WACHH299 

WACHH384 

WACHH427 

WACHH440 

WACHH604 

1301M28G08 ............................ WACAR292 

WACAR354 

(g) Table 2 of this AD lists the P/Ns and 

SNs of the weld-repaired forward engine 

mount platforms that have a weld repair in 

a redundant area of the mount. Because it is 

impossible to detect whether the mount is 

operating on the redundant feature, each of 

these mounts must be replaced. The 

compliance time for mounts in this category 

can be longer than for the mounts listed in 

Table 1 of this AD. 

TABLE 2.—WELD-REPAIRED FORWARD

ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE

A WELD REPAIR IN A REDUNDANT

AREA OF THE MOUNT

P/Ns SNs 

1292M13G06 or 1846M24G04 WACHH173 

WACHH189 

WACHH274 

TABLE 2.—WELD-REPAIRED FORWARD

ENGINE MOUNT PLATFORMS REQUIRING REPLACEMENT THAT HAVE

A WELD REPAIR IN A REDUNDANT

AREA OF THE MOUNT—Continued 

P/Ns SNs 

WACHH278 

WACHH314 

WACHH325 

WACHH486 

1301M28G08 ............................ WACAR294 

WACAR304 

WACAR353 

WACAR372 

1459M70G07 ............................ MTXT1282 

(h) Table 3 of this AD lists the P/Ns and 

SNs of the weld-repaired forward engine 

mount yokes that have a weld repair in a 

redundant area of the yoke. Because it is 

impossible to detect whether the mount yoke 

is operating on the redundant feature, each 

of these mount yokes must be replaced. The 

compliance time for mounts in this category 

can be longer than for the mounts listed in 

Table 1 of this AD. 

TABLE 3.—WELD-REPAIRED FORWARD

ENGINE MOUNT YOKES REQUIRING

REPLACEMENT THAT HAVE A WELD

REPAIR IN A NON-REDUNDANT AREA

OF THE YOKE

P/Ns SNs 

9383M43G14 ............................ WACV0388 

WACV0394 

WACV0405 

WACV0406 

WACV0477 

WACV0498 

WACV0529 

WACV0556 

WACV0579 

WACV0581 

WACV0582 

WACV0600 

WACV0605 

WACV0617 

WACV0625 

WACV0627 

WACV0633 

WACV0645 

WACV0683 

WACV0703 

WACV0733 

WACV0737 

WACV0759 

WACV0775 

WACV0791 

WACV0799 

WACV0875 

WACV0883 

WACV0885 

WACV0909 

WACV1097 

WACV1615 

WACV1713 

WACV1753 

WACV1797 

WACV1867 

WACV1987 

TABLE 3.—WELD-REPAIRED FORWARD

ENGINE MOUNT YOKES REQUIRING

REPLACEMENT THAT HAVE A WELD

REPAIR IN A NON-REDUNDANT AREA

OF THE YOKE—Continued 

P/Ns SNs 

WACV2131 

WACV2159 

WACV2185 

WACV2343 

WACV2511 

WACV2695 

WACV2707 

WACV2881 

WACV2899 

9383M43G16 ............................ WACV0511 

WACV0515 

WACV0518 

WACV0540 

WACV0542 

WACV0571 

WACV0689 

WACV0721 

WACV0727 

WACV0730 

WACV0786 

WACV0816 

WACV0954 

(i) GE advises that forward engine mount 

platform, P/Ns 1292M13G06 and 

1846M24G04, are the same, except that P/N 

1846M24G04 incorporates a previously 

approved field rework. This rework allows 

the thrust pin hole in the forward engine 

mount platform to be bored out to accept 

installation of an oversized thrust pin. GE 

cannot identify which SN goes with which P/ 

N, but all SNs are affected. 

Welded Cast Titanium Forward Engine 

Mount Platform and Forward Engine Mount 

Yoke Removal 

(j) If the P/N and SN of the forward engine 

mount platform listed in Table 1 and Table 

2 and the forward engine mount yoke listed 

in Table 3 of this AD are not installed on the 

engine, no further action is necessary. 

(k) If the P/N and SN of the forward engine 

mount platform listed in Table 1 of this AD 

is installed on the engine: 

(1) Remove the forward engine mount 

platform from the engine within 500 cycles 

or 6 months, after the effective date of this 

AD, whichever occurs first. 

(2) Information for removal of the forward 

engine mount platform from the engine can 

be found in the CF6–80C2 Engine Manual, 

72–00–01, Disassembly. 

(l) If the P/N and SN of the forward engine 

mount platform listed in Table 2 of this AD 

is installed on the engine: 

(1) Remove the forward engine mount 

platform at the next shop visit, or within 

4,800 cycles after the effective date of this 

AD, whichever occurs first. 

(2) Information for removal of the forward 

engine mount yoke can be found in the CF6–

80C2 Engine Manual, 72–00–01, 

Disassembly. 

(m) If the P/N and SN of the forward 

engine mount yoke listed in Table 3 of this 

AD is installed on the engine: 


jlentini on PROD1PC65 with PROPOSAL
74876 Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules 

(1) Remove the forward engine mount yoke 

at the next shop visit, or within 4,800 cycles 

after the effective date of this AD, whichever 

occurs first. 

(2) Information for removal of the forward 

engine mount yoke can be found in the CF6–

80C2 Engine Manual, 72–00–01, 

Disassembly. 

(n) Replace the affected forward engine 

mount platform and or the affected forward 

engine mount yoke with a non-weld-repaired 

cast titanium forward engine mount platform 

and or the forward engine mount yoke or a 

forged titanium forward engine mount 

platform or a forged titanium forward engine 

mount yoke. 

(o) Information for installing the forward 

engine mount platform and forward engine 

mount yoke can be found in the CF6–80C2 

Engine Manual, 72–00–01, Assembly. 

(p) Location of the forward engine mount 

platform and forward engine mount yoke and 

SN are illustrated in the following Figure 1. 

BILLING CODE 4910–13–P 


jlentini on PROD1PC65 with PROPOSAL
Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules 74877 

BILLING CODE 4910–13–C (q) After the effective date of this AD, do 

not install a weld-repaired, cast forward 

engine mount platform or a weld-repaired, 


jlentini on PROD1PC65 with PROPOSALEP13DE06.002</GPH>
74878 Federal Register / Vol. 71, No. 239 / Wednesday, December 13, 2006 / Proposed Rules 

cast forward engine mount yoke in any 

engine. 

Alternative Methods of Compliance 

(r) The Manager, Engine 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. 

Issued in Burlington, Massachusetts, on 

December 7, 2006. 

Robert Ganley, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 06–9674 Filed 12–12–06; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–20856; Directorate 

Identifier 2004–NE–25–AD] 

RIN 2120–AA64 

Airworthiness Directives; MT-Propeller 

Entwicklung GmbH Propellers 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: The FAA proposes to 

supersede an existing airworthiness 

directive (AD) for certain MT-Propeller 

Entwicklung GmbH variable pitch and 

fixed pitch propellers manufactured 

before 1995 which had not been 

overhauled since April 1994. That AD 

currently requires overhauling the 

propeller blades and performing initial 

and repetitive visual inspections of 

affected propeller blades. That AD also 

requires removing all propeller blades 

from service with damaged erosion 

sheath bonding or loose erosion sheaths 

and installing any missing or damaged 

polyurethane protective strips. This 

proposed AD would require the same 

actions. This proposed AD results from 

the need to clarify the population of 

affected propellers previously listed in 

AD 2006–05–05. We are proposing this 

AD to prevent erosion sheath separation 

leading to damage of the airplane. 

DATES: We must receive any comments 

on this proposed AD by February 12, 

2007. 

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. 

Contact MT-Propeller USA, Inc., 1180 

Airport Terminal Drive, Deland, FL 

32724; telephone (386) 736–7762, fax 

(386) 736–7696 or visit http://www.mtpropeller.com for the service 

information identified in this proposed 

AD. 

FOR FURTHER INFORMATION CONTACT: 

Frank Walsh, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, Engine and Propeller Directorate, 

12 New England Executive Park, 

Burlington, MA 01803–5299; telephone 

(781) 238–7158, fax (781) 238–7170. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments 

regarding this proposal. Send your 

comments to an address listed under 

ADDRESSES. Include ‘‘Docket No. FAA–

2005–20856; Directorate Identifier 

2004–NE–25–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 DMS 

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 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 DMS Docket Office 

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

through Friday, except Federal holidays. 

The Docket Office (telephone (800) 647–

5227) is located on the plaza level of the 

Department of Transportation Nassif 

Building at the street address stated in 

ADDRESSES. Comments will be available 

in the AD docket shortly after the DMS 

receives them. 

Discussion 

On February 24, 2006, we issued AD 

2006–05–05, Amendment 39–14502 (71 

FR 11151, March 6, 2006). That AD 

requires overhaul of models MT, MTV–

1, MTV–2, MTV–3, MTV–5, MTV–6, 

MTV–7, MTV–9, MTV–10, MTV–11, 

MTV–12, MTV–14, MTV–15, MTV–17, 

MTV–18, MTV–20, MTV–21, MTV–22, 

MTV–24, and MTV–25 propellers with 

serial numbers (SNs) below 95000, 

which had not been overhauled since 

April 1994, within 30 days after the 

effective date of the AD. That action also 

required performing initial and 

repetitive visual inspections of those 

propeller blades. That action also 

required removing all propeller blades 

from service with damaged erosion 

sheath bonding or loose erosion sheaths 

and to install any missing or damaged 

polyurethane protective strips. The 

European Aviation Safety Agency 

(EASA), which is the airworthiness 

authority for the European Union, 

notified us that an unsafe condition may 

exist on certain MT-Propeller 

Entwicklung GmbH propellers. 

Actions Since AD 2006–05–05 Was 

Issued 

Since AD 2006–05–05 was issued, 

MT-Propeller Entwicklung GmbH 

Propellers and EASA have clarified the 

population of affected propellers. AD 

2006–05–05 described the affected 

propellers as variable pitch and fixed 

pitch propellers with serial numbers 

(SNs) below 95000. Because propellers 

with SNs starting with 00, 01, 02, 03, 04, 

05, and 06, were manufactured in the 

years 2000, 2001, 2002, 2003, 2004, 

2005, and 2006 respectively, some 

operators are confused as to whether 

their propeller SN is part of the affected 

population. For example, propeller SN 

00246, manufactured in 2000, would 

appear to be part of the affected 

population because the number is below 

95000. For clarification, we are 

proposing to identify the affected 

population as variable pitch and fixed 

pitch propellers manufactured before 


jlentini on PROD1PC65 with PROPOSAL