Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 5681 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane. 

(4) Alternative methods of compliance, 

approved previously in accordance with AD 

2003–03–02, for the actions specified in 

paragraph (i) of that AD, are approved as 

alternative methods of compliance with 

paragraph (h) of this AD. 

Material Incorporated by Reference 

(s) You must use Boeing Alert Service 

Bulletin 767–54A0062, Revision 6, dated 

November 5, 2009, to do the actions required 

by this AD, unless the AD specifies 

otherwise. If you accomplish the optional 

actions specified by this AD, you must use 

the service information specified in Table 1 

of this AD to do those actions, unless the AD 

specifies otherwise. 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE FOR OPTIONAL TERMINATING ACTION IN THIS AD 

Boeing Service Bulletin— Revision— Dated— 

767–54–0069 ............................................................................. Original ................................................................... October 9, 1997. 

767–54–0069 ............................................................................. 1 ............................................................................. January 29, 1998. 

767–54–0069 ............................................................................. 2 ............................................................................. August 31, 2000. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Boeing Alert Service Bulletin 767–54A0062, 

Revision 6, dated November 5, 2009; and 

Boeing Service Bulletin 767–54–0069, dated 

October 9, 1997; under 5 U.S.C. 552(a) and 

1 CFR part 51. 

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Service Bulletin 767–57– 

0069, Revision 2, dated August 31, 2000, on 

March 5, 2001 (66 FR 8085, January 29, 

2001). 

(3) The Director of the Federal Register 

previously approved the incorporation by 

reference of Boeing Service Bulletin 767–54– 

0069, Revision 1, dated January 29, 1998, on 

October 17, 2000 (65 FR 58641, October 2, 

2000). 

(4) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(5) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(6) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Renton, Washington, on January 

22, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–2192 Filed 2–3–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0065; Directorate 

Identifier 2009–SW–01–AD; Amendment 39– 

16186; AD 2010–03–03] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. Model 205B 

and 212 Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

Bell Helicopter Textron, Inc. (Bell) 

Model 205B and 212 helicopters with 

certain main rotor (M/R) blade 

assemblies installed. This action 

requires inspecting the M/R blades 

paying particular attention to an area 

near the blade root for an edge void, 

corrosion, or a crack. This amendment 

is prompted by two reports of fatigue 

cracks on M/R blades installed on 

Model 212 helicopters. Both model 

helicopters use the same part-numbered 

M/R blades. The actions specified in 

this AD are intended to detect an edge 

void, corrosion, or a crack on a M/R 

blade, which could lead to loss of the 

M/R blade and subsequent loss of 

control of the helicopter. 

DATES: Effective February 19, 2010. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of February 

19, 2010. 

Comments for inclusion in the Rules 

Docket must be received on or before 

April 5, 2010. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

AD: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

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

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. You may get 

the service information identified in this 

AD from Bell Helicopter Textron, Inc., 

P.O. Box 482, Fort Worth, TX 76101, 

telephone (817) 280–3391, fax (817) 

280–6466, or at http:// 

www.bellcustomer.com/files/. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov, or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The Docket 

Operations office (telephone (800) 647– 

5527) is located in Room W12–140 on 

the ground floor of the West Building at 

the street address stated in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Michael 

Kohner, ASW–170, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Rotorcraft Certification Office, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax 

(817) 222–5783. 

SUPPLEMENTARY INFORMATION: This 

amendment adopts a new AD for certain 

serial-numbered Bell Model 205B and 

212 helicopters with a M/R blade, part 

number (P/N) 212–015–501–005, –111, 

–113, –115, –117, –119, or –121, 

installed. The AD requires, within 25 


cprice-sewell on DSK2BSOYB1PROD with RULES
5682 Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 

hours time-in-service (TIS), and 

thereafter at intervals not to exceed 100 

hours TIS, washing the upper and lower 

surfaces of each M/R blade and visually 

inspecting the grip plates and doublers 

in the area between blade stations 24.5 

and 40.0 for an edge void, corrosion, or 

a crack, using a 3x power or higher 

magnifying glass. It also requires 

visually inspecting the remaining 

surfaces of each M/R blade in the area 

between blade stations 24.5 and 40.0 for 

any corrosion or a crack using a 3x 

power or higher magnifying glass. If a 

crack is found in the paint finish, 

removing the paint and re-inspecting 

the M/R blade is required before further 

flight. If a crack is found in the M/R 

blade, replacing it with an airworthy M/ 

R blade is required before further flight. 

If an edge void or any corrosion is found 

in the M/R blade, replacing it with an 

airworthy M/R blade, or repairing it if 

the damage is within the maximum 

repair damage limits, is required before 

further flight. This amendment is 

prompted by two reports of fatigue 

cracks on M/R blades installed on 

Model 212 helicopters. The cracks were 

located in the lower doublers and skin, 

and the box beam at the M/R blade 

attachment bolt hole, and in the lower 

grip plate at blade station (BS) 36. The 

M/R blades had accumulated 1,026 and 

2,559 hours TIS. The cause of the cracks 

has been attributed to inadequate 

adhesive bonding during manufacture 

in the area between the grip plate and 

mating doubler surface. A crack first 

appears in the grip plate, which can be 

detected visually with the M/R blade 

installed on the helicopter. The actions 

specified in this AD are intended to 

detect an edge void, corrosion, or a 

crack on a M/R blade, which could lead 

to loss of the M/R blade and subsequent 

loss of control of the helicopter. 

We have reviewed Bell Helicopter 

Alert Service Bulletin (ASB) No. 205B– 

08–51 and ASB No. 212–08–130, both 

Revision A, dated January 13, 2009, 

applicable to Model 205B and Model 

212 helicopters, respectively, which 

describe procedures for initial and 

repetitive inspections of certain partnumbered M/R blades on certain serialnumbered helicopters for signs of an 

edge void, corrosion, or a crack, 

including a hair-line crack in the M/R 

blade paint finish. 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design. Therefore, this AD is 

being issued to detect an edge void, 

corrosion, or a crack on a M/R blade, 

which could lead to loss of the M/R 

blade and subsequent loss of control of 

the helicopter. Accomplish the actions 

by following specified portions of the 

applicable ASB, described previously. 

The short compliance time involved is 

required because the previously 

described critical unsafe condition can 

adversely affect the structural integrity 

and controllability of the helicopter. 

Therefore, the AD must be issued 

immediately to require the following 

actions within 25 hours TIS, and 

thereafter at intervals not to exceed 100 

hours TIS: 

• Washing the upper and lower M/R 

blade surfaces using a solution of 

cleaning compound (C–318) and water; 

• Using a 3x or higher magnifying 

glass, visually inspecting the upper and 

lower grip plates and doublers of the M/ 

R blade between blade station (BS) 24.5 

to 40, and the whole width of the chord, 

for an edge void, any corrosion, or a 

crack; 

• Using a 3x power or higher 

magnifying glass, visually inspecting the 

remaining upper and lower surfaces of 

the M/R blade between BS 24.5 and 

40.0, and the whole width of the chord, 

for any corrosion or a crack; 

• Applying a light coat of 

preservative oil (C–125) to all surfaces 

of the M/R blade; 

• Removing paint from areas in 

which a crack is discovered in the M/ 

R blade paint finish by sanding with 

180–220 grit paper to determine if a 

crack exists in the M/R blade; 

• Replacing any M/R blade that has a 

crack in any part of the M/R blade other 

than the paint finish with an airworthy 

M/R blade; 

• Replacing any M/R blade that has 

any corrosion or an edge void with an 

airworthy M/R blade, or repairing the 

M/R blade if the damage is within the 

maximum repair damage limits. The 

maximum repair damage limitations are 

contained in the applicable Component 

and Repair Overhaul Manual; and 

• Replacing any M/R blade that has 

any parent material removed during the 

sanding operation to remove paint from 

areas in which a paint crack is 

discovered, or repairing the M/R blade 

if the amount of parent removed 

material is within the maximum repair 

damage limits. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

We estimate that this AD will affect 

87 helicopters of U.S. registry, and 

washing and visually inspecting each 

M/R blade will take approximately 1 

work hour per helicopter at an average 

labor rate of $80 per work hour. If an 

edge void, corrosion, or a crack is 

discovered, replacing the M/R blade 

with an airworthy blade will take 

approximately 6 work hours. Required 

parts will cost approximately $97,500 

for a replacement M/R blade. Based on 

these figures, we estimate the total cost 

impact of the AD on U.S. operators to 

be $139,740, assuming that 6 

inspections per year are conducted on 

each helicopter, and that one M/R blade 

will need to be replaced. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2010–0065; 

Directorate Identifier 2009–SW–01–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact with FAA 

personnel concerning this AD. Using the 

search function of our docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national Government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the 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. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 


cprice-sewell on DSK2BSOYB1PROD with RULES
Federal Register / Vol. 75, No. 23 / Thursday, February 4, 2010 / Rules and Regulations 5683 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD. See the AD docket to examine 

the economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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. Section 39.13 is amended by adding 

a new airworthiness directive to read as 

follows: 

2010–03–03 Bell Helicopter Textron, Inc.: 

Amendment 39–16186. Docket No. 

FAA–2010–0065; Directorate Identifier 

2009–SW–01–AD. 

Applicability: Serial-numbered Model 

205B and Model 212 helicopters, with the 

specified part-numbered main rotor (M/R) 

blade that is listed in Table 1 of this AD 

installed, certificated in any category. 

TABLE 1 

Helicopter model and serial No. (S/N) M/R blade P/N 

Model 205B: S/N 30066, 30166, 30188, or 30297 ........................................... P/N 212–015–501–005, –111, –113, –115, –117, –119, or –121. 

Model 212: S/N 30502 through 30603, 30611 through 30999, 31101 through 

31311, 32101 through 32262, or 35001 through 35103.

P/N 212–015–501–005, –111, –113, –115, –117, –119, or – 121. 

Compliance: Required as indicated. 

To detect an edge void, corrosion, or a 

crack on a M/R blade, which could lead to 

loss of the M/R blade and subsequent loss of 

control of the helicopter, accomplish the 

following: 

(a) Within 25 hours time-in-service (TIS), 

unless accomplished previously, and 

thereafter at intervals not to exceed 100 hours 

TIS: 

(1) Wash the upper and lower surfaces of 

the M/R blade with a solution of cleaning 

compound (C–318) and water. Rinse 

thoroughly and wipe dry. 

(2) Using a 3x power or higher magnifying 

glass, on each affected M/R blade, in an area 

from blade stations 24.5 to 40, including the 

entire width of the M/R blade chord, as 

depicted in Figure 1 in Bell Helicopter Alert 

Service Bulletin No. 205B–08–51 for the 

Model 205B helicopters, or No. 212–08–130 

for the Model 212 helicopters, both Revision 

A, dated January 13, 2009 (ASBs), as 

applicable: 

(i) Visually inspect the upper and lower 

grip plates and doublers of the M/R blade in 

the specified area for an edge void, corrosion, 

or a crack. 

(ii) Visually inspect the remaining upper 

and lower surfaces of the M/R blade in the 

specified area for any corrosion or a crack. 

Note 1: The inspections required by 

paragraphs (a)(2)(i) and (a)(2)(ii) of this AD 

can be accomplished with the M/R blade 

installed on the helicopter. 

Note 2: Crack indications on an actual 

M/R blade are shown in Figure 2 of both 

ASBs. 

(3) Apply a light coat of preservative oil 

(C–125) to all surfaces of the M/R blade in 

the specified area. 

(b) Before further flight: 

(1) If any corrosion or an edge void is 

found, replace the M/R blade with an 

airworthy M/R blade, or repair the M/R blade 

if the damage is within the maximum repair 

damage limits. 

(2) If a crack is found in the M/R blade 

paint finish, remove the paint in the affected 

area by lightly sanding with 180–220 grit 

paper in a span wise direction to determine 

if the grip plate, doubler, or skin is cracked. 

Do not remove any parent material of the 

M/R blade during the sanding operation. 

Refinish the sanded area. 

(3) If a crack is found in any part of the 

M/R blade other than the paint finish, replace 

the M/R blade with an airworthy M/R blade. 

(4) If any parent material is removed 

during the sanding operation required by 

paragraph (b)(2) of this AD, replace the 

M/R blade with an airworthy M/R blade, or 

repair the M/R blade if the amount of parent 

material removed is within the maximum 

repair damage limits. 

Note 3: The maximum repair damage 

limitations specified in paragraphs (b)(1) 

through (b)(4) of this AD are contained in the 

applicable Component and Repair Overhaul 

Manual. 

(c) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Rotorcraft 

Certification Office, ATTN: Michael Kohner, 

Aviation Safety Engineer, FAA, Rotorcraft 

Directorate, 2601 Meacham Blvd., Fort 

Worth, Texas 76137, telephone (817) 222– 

5170, fax (817) 222–5783, for information 

about previously approved alternative 

methods of compliance. 

(d) The inspections and replacements, if 

necessary, shall be done in accordance with 

the specified portions of Bell Helicopter Alert 

Service Bulletin No. 205B–08–51 for Model 

205B helicopters, or No. 212–08–130 for 

Model 212 helicopters, both Revision A, 

dated January 13, 2009, as applicable. The 

Director of the Federal Register approved this 

incorporation by reference in accordance 

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

Copies may be obtained from Bell Helicopter 

Textron, Inc., P.O. Box 482, Fort Worth, TX 

76101, telephone (817) 280–3391, fax (817) 

280–6466, or at http:// 

www.bellcustomer.com/files/. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas or at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Joint Aircraft System/Component (JASC) 

Code 

(e) JASC Code 6210: Main Rotor Blades. 

(f) This amendment becomes effective on 

February 19, 2010. 

Issued in Fort Worth, Texas, on 

December 21, 2009. 

Scott A. Horn, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–1720 Filed 2–3–10; 8:45 am] 

BILLING CODE 4910–13–P 


cprice-sewell on DSK2BSOYB1PROD with RULES