Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 423 

Service Bulletin A310–27–2099, Revision 01, 

dated March 21, 2008. 

(1) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done before the effective date of this AD: 

Within 400 flight cycles after accomplishing 

the inspection. 

(2) For airplanes on which the inspection 

required by paragraph (g) of this AD has been 

done on or after the effective date of this AD: 

Within 400 flight hours after accomplishing 

the inspection required by paragraph (g) of 

this AD. 

New Requirements of This AD 

Actions 

(i) Accomplishment of the actions required 

by paragraph (h) do not terminate the 

repetitive inspections required by paragraph 

(g) of this AD. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, Transport Airplane Directorate, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–2125; fax (425) 

227–1149. Before using any approved AMOC 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. AMOCs 

approved previously in accordance with AD 

2007–02–22, Amendment 39–14909, are 

approved as AMOCs for the corresponding 

provisions of paragraphs (g) and (h) of this 

AD. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency Airworthiness Directive 2006– 

0111R1, dated August 26, 2009; and Airbus 

Mandatory Service Bulletin A310–27–2099, 

Revision 01, dated March 21, 2008; for 

related information. 

Material Incorporated by Reference 

(l) You must use Airbus Mandatory Service 

Bulletin A310–27–2099, Revision 01, dated 

March 21, 2008, to do the actions required by 

this AD, unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Airbus Mandatory Service Bulletin A310–27– 

2099, Revision 01, dated March 21, 2008, 

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

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; e-mail: account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(3) 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. 

(4) 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 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32987 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0701; Directorate 

Identifier 2010–NM–017–AD; Amendment 

39–16561; AD 2011–01–08] 

RIN 2120–AA64 

Airworthiness Directives; Fokker 

Services B.V. Model F.28 Mark 0100 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) 

that applies to the products listed above. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The MCAI describes 

the unsafe condition as: 

Two reports have been received where, 

during inspection of the vertical stabilizer of 

F28 Mark 0100 aeroplanes, one of the bolts 

that connect the horizontal stabilizer control 

unit actuator with the dog-links was found 

broken (one on the nut side & one on the 

head side). In both occasions, the bolt shaft 

was still present in the connection and 

therefore the horizontal stabilizer function 

was not affected. If a single dog-link 

connection fails, the complete stabilizer load 

is taken up by the remaining dog-link 

connection. * * * 

To address and correct this unsafe 

condition EASA [European Aviation Safety 

Agency] issued AD 2007–0287 

[corresponding FAA AD 2008–22–14] that 

required a one-time inspection of the affected 

bolts, * * * and replacement of failed bolts 

with serviceable parts. EASA AD 2007–0287 

also required the installation of a tie wrap 

through the lower bolts of the horizontal 

stabilizer control unit, to keep the bolt in 

place in the event of a bolt head failure. 

Recent examination revealed that the bolts 

failed due to stress corrosion, attributed to 

excessive bolt torque. Investigation of the 

recently failed bolts showed that the 

modification as required by AD 2007–0287 is 

not adequate. 

* * * * * 

Loss of horizontal stabilizer function 

could result in partial loss of control of 

the airplane. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

February 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 9, 2011. 

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424 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of December 26, 2008 (73 FR 

70261, November 20, 2008). 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue, SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: Tom 

Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1137; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on July 27, 2010 (75 FR 43876), 

and proposed to supersede AD 2008– 

22–14, Amendment 39–15710 (73 FR 

70261, November 20, 2008). That NPRM 

proposed to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Two reports have been received where, 

during inspection of the vertical stabilizer of 

F28 Mark 0100 aeroplanes, one of the bolts 

that connect the horizontal stabilizer control 

unit actuator with the dog-links was found 

broken (one on the nut side & one on the 

head side). In both occasions, the bolt shaft 

was still present in the connection and 

therefore the horizontal stabilizer function 

was not affected. If a single dog-link 

connection fails, the complete stabilizer load 

is taken up by the remaining dog-link 

connection. Any failed connection should be 

detected and corrected at the next scheduled 

inspection. 

To address and correct this unsafe 

condition EASA [European Aviation Safety 

Agency] issued AD 2007–0287 

[corresponding FAA AD 2008–22–14] that 

required a one-time inspection of the affected 

bolts, Part Number (P/N) 23233–1, and 

replacement of failed bolts with serviceable 

parts. EASA AD 2007–0287 also required the 

installation of a tie wrap through the lower 

bolts of the horizontal stabilizer control unit, 

to keep the bolt in place in the event of a bolt 

head failure. 

Recent examination revealed that the bolts 

failed due to stress corrosion, attributed to 

excessive bolt torque. Investigation of the 

recently failed bolts showed that the 

modification as required by AD 2007–0287 is 

not adequate. 

To address the stress corrosion, the 

manufacturer of the bolt, Goodrich, has 

introduced a bolt with an improved corrosion 

protection, P/N 23233–3, through Service 

Bulletin 23100–27–29. 

For the reasons described above, this EASA 

AD retains the requirements of AD 2007– 

0287, which is superseded, and adds the 

requirement to replace the affected P/N 

23233–1 bolts with improved bolts. 

Concurrently, the tie-wrap must be removed. 

Loss of horizontal stabilizer function 

could result in partial loss of control of 

the airplane. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 4 products of U.S. registry. 

The actions that are required by AD 

2008–22–14 and retained in this AD 

take about 3 work-hours per product, at 

an average labor rate of $85 per workhour. Based on these figures, the 

estimated cost of the currently required 

actions is $255 per product. 

We estimate that it will take about 7 

work-hours per product to comply with 

the new basic requirements of this AD. 

The average labor rate is $85 per workhour. Required parts will cost about 

$1,550 per product. Where the service 

information lists required parts costs 

that are covered under warranty, we 

have assumed that there will be no 

charge for these costs. As we do not 

control warranty coverage for affected 

parties, some parties may incur costs 

higher than estimated here. Based on 

these figures, we estimate the cost of 

this AD to the U.S. operators to be 

$8,580, or $2,145 per product. 

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 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 this AD: 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket 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 AD docket 

contains the NPRM, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

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Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 425 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–15710 (73 FR 

70261, November 20, 2008) and adding 

the following new AD: 

2011–01–08 Fokker Services B.V.: 

Amendment 39–16561. Docket No. 

FAA–2010–0701; Directorate Identifier 

2010–NM–017–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 9, 2011. 

Affected ADs 

(b) This AD supersedes AD 2008–22–14, 

Amendment 39–15710. 

Applicability 

(c) This AD applies to Fokker Services B.V. 

Model F.28 Mark 0100 airplanes, certificated 

in any category, all serial numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight Controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Two reports have been received where, 

during inspection of the vertical stabilizer of 

F28 Mark 0100 aeroplanes, one of the bolts 

that connect the horizontal stabilizer control 

unit actuator with the dog-links was found 

broken (one on the nut side & one on the 

head side). In both occasions, the bolt shaft 

was still present in the connection and 

therefore the horizontal stabilizer function 

was not affected. If a single dog-link 

connection fails, the complete stabilizer load 

is taken up by the remaining dog-link 

connection. * * * 

To address and correct this unsafe 

condition EASA [European Aviation Safety 

Agency] issued AD 2007–0287 

[corresponding FAA AD 2008–22–14] that 

required a one-time inspection of the affected 

bolts, * * * and replacement of failed bolts 

with serviceable parts. EASA AD 2007–0287 

also required the installation of a tie wrap 

through the lower bolts of the horizontal 

stabilizer control unit, to keep the bolt in 

place in the event of a bolt head failure. 

Recent examination revealed that the bolts 

failed due to stress corrosion, attributed to 

excessive bolt torque. Investigation of the 

recently failed bolts showed that the 

modification as required by AD 2007–0287 is 

not adequate. 

* * * * * 

Loss of horizontal stabilizer function could 

result in partial loss of control of the 

airplane. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Restatement of Requirements of AD 2008– 

22–14 

Actions and Compliance 

(g) Unless already done, within 6 months 

after December 26, 2008 (the effective date of 

AD 2008–22–14), do the following actions. 

(1) Perform a one-time inspection (integrity 

check) for failure of the lower bolts of the 

stabilizer control unit dog-links, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–27–091, dated August 31, 2007. If a 

failed bolt is found, before further flight, 

replace the bolt with a serviceable bolt in 

accordance with the Accomplishment 

Instructions of that service bulletin. 

(2) Install a tie-wrap through the lower 

bolts of the stabilizer control unit, in 

accordance with the Accomplishment 

Instructions of Fokker Service Bulletin 

SBF100–27–091, dated August 31, 2007. 

New Requirements of This AD 

Actions 

(h) Within 30 months after the effective 

date of this AD, do the actions specified in 

paragraphs (h)(1) and (h)(2) of this AD 

concurrently. Accomplishing the actions of 

both paragraphs (h)(1) and (h)(2) of this AD 

terminates the actions required by paragraph 

(g) of this AD. 

(1) Remove the tie-wrap, P/N MS3367–2– 

9, from the lower bolts of the horizontal 

stabilizer control unit, in accordance with the 

Accomplishment Instructions of Fokker 

Service Bulletin SBF100–27–092, dated April 

27, 2009. 

(2) Remove the lower bolts, P/N 23233–1, 

of the horizontal stabilizer control unit and 

install bolts, P/N 23233–3, in accordance 

with the Accomplishment Instructions of 

Goodrich Service Bulletin 23100–27–29, 

dated November 14, 2008. 

(i) After accomplishing the requirements of 

paragraph (h) of this AD, do not install a bolt 

having P/N 23233–1 or a tie-wrap having 

P/N MS3367–2–9. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

Send information to ATTN: Tom Rodriguez, 

Aerospace Engineer, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

227–1137; fax (425) 227–1149. Before using 

any approved AMOC on any airplane to 

which the AMOC applies, notify your 

principal maintenance inspector (PMI) or 

principal avionics inspector (PAI), as 

appropriate, or lacking a principal inspector, 

your local Flight Standards District Office. 

The AMOC approval letter must specifically 

reference this AD. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(k) Refer to MCAI EASA Airworthiness 

Directive 2009–0216, dated October 7, 2009; 

Fokker Service Bulletin SBF100–27–091, 

dated August 31, 2007; Fokker Service 

Bulletin SBF100–27–092, dated April 27, 

2009; and Goodrich Service Bulletin 23100– 

27–29, dated November 14, 2008; for related 

information. 

Material Incorporated by Reference 

(l) You must use the applicable service 

information contained in Table 1 of this AD 

to do the actions required by this AD, unless 

the AD specifies otherwise. 

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426 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 

TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE

Document Date 

Fokker Service Bulletin SBF100–27–091 ................................................................................................................................ August 31, 2007. 

Fokker Service Bulletin SBF100–27–092 ................................................................................................................................ April 27, 2009. 

Goodrich Service Bulletin 23100–27–29 ................................................................................................................................. November 14, 2008. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Fokker Service Bulletin SBF100–27–092, 

dated April 27, 2009; and Goodrich Service 

Bulletin 23100–27–29, dated November 14, 

2008; 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 Fokker Service Bulletin SBF100– 

27–091, dated August 31, 2007, on December 

26, 2008 (73 FR 70261, November 20, 2008). 

(3) For Fokker service information 

identified in this AD, contact Fokker Services 

B.V., Technical Services Dept., P.O. Box 231, 

2150 AE Nieuw-Vennep, the Netherlands; 

telephone +31 (0)252–627–350; fax +31 

(0)252–627–211; e-mail 

technicalservices.fokkerservices@stork.com; 

Internet http://www.myfokkerfleet.com. For 

Goodrich service information identified in 

this AD, contact Goodrich Corporation, 

Landing Gear, 1400 South Service Road, 

West Oakville L6L 5Y7, Ontario, Canada; 

telephone 905–825–1568; e-mail 

jean.breed@goodrich.com; Internet http:// 

www.goodrich.com/TechPubs. 

(4) 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. 

(5) 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 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32990 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0855; Directorate 

Identifier 2010–NM–066–AD; Amendment 

39–16566; AD 2011–01–12] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 737–300, –400, and 

–500 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

the products listed above. That AD 

currently requires repetitive inspections 

for discrepancies of the fuse pins of the 

inboard and outboard midspar fittings of 

the nacelle strut, and corrective actions 

if necessary. This new AD requires 

replacing the midspar fuse pins with 

new, improved fuse pins, which would 

terminate the repetitive inspections. 

This AD was prompted by a report of 

corrosion damage of the chrome runout 

on the head side found on all four 

midspar fuse pins of the nacelle strut. 

Additionally, a large portion of the 

chrome plate was missing from the 

corroded area of the shank. We are 

issuing this AD to prevent damage of the 

fuse pins of the inboard and outboard 

midspar fittings of the nacelle strut, 

which could result in reduced structural 

integrity of the fuse pins, and 

consequent loss of the strut and 

separation of the engine from the 

airplane. 

DATES: This AD is effective February 9, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of November 13, 2008 (73 FR 

59493, October 9, 2008). 

ADDRESSES: 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. You 

may review copies of the referenced 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6450; fax (425) 917–6590; 

e-mail: alan.pohl@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede airworthiness 

directive (AD) 2008–21–03, Amendment 

39–15687 (73 FR 59493, October 9, 

2008). That AD applies to the specified 

products. The NPRM published in the 

Federal Register on September 23, 2010 

(75 FR 57882). That NPRM proposed to 

continue to require repetitive 

inspections for discrepancies of the fuse 

pins of the inboard and outboard 

midspar fittings of the nacelle strut, and 

corrective actions if necessary. That 

NPRM also proposed to require 

replacing the midspar fuse pins with 

new, improved fuse pins, which would 

terminate the requirement for repetitive 

detailed inspections. 

WReier-Aviles on DSKGBLS3C1PROD with RULES