Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 24349 

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. 

(3) For Smiths and GE Aviation service 

information identified in this AD, contact GE 

Aviation, Customer Support Center, 1 

Neumann Way, Cincinnati, Ohio 45215; 

telephone 513–552–3272; e-mail 

cs.techpubs@ge.com; Internet http:// 

www.geaviation.com. 

(4) You may review copies of the service 

information at the FAA, 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 an NARA facility, 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 April 8, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–9917 Filed 4–29–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1111; Directorate 

Identifier 2010–NM–129–AD; Amendment 

39–16676; AD 2011–09–14] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200B, –300, –400, 

–400D, and –400F Series Airplanes 

Powered by Pratt and Whitney 4000 or 

General Electric CF6–80C2 Series 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

an inspection to determine the part 

number of the mid-pivot access door 

and to determine if the correct door is 

installed, and the installation of a 

marker on the mid-pivot access door, 

and if necessary, repetitive ultrasonic 

inspections for cracking of the midpivot bolt assembly and eventual 

replacement of the mid-pivot bolt 

assembly. This AD was prompted by a 

report that the left and right access 

doors of the spring beam mid-pivot bolt 

assembly for the No. 1 strut were 

inadvertently installed in the incorrect 

position during strut modification. We 

are issuing this AD to detect and correct 

incorrectly installed mid-pivot bolt 

assemblies on the spring beam on the 

outboard struts. Incorrectly installed 

bolt assemblies could lead to fatigue 

cracking and consequent fracturing of 

the mid-pivot bolt assembly, which 

could lead to loss of the spring beam 

load path and the possible separation of 

a strut and engine from the airplane 

during flight. 

DATES: This AD is effective June 6, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 6, 2011. 

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: 

Kenneth Paoletti, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6434; fax (425) 917–6590; e-mail: 

Kenneth.Paoletti@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 

November 15, 2010 (75 FR 69612). That 

NPRM proposed to require an 

inspection to determine the part number 

of the mid-pivot access door and to 

determine if the correct door is 

installed, and the installation of a 

marker on the mid-pivot access door, 

and if necessary, repetitive ultrasonic 

inspections for cracking of the midpivot bolt assembly and eventual 

replacement of the mid-pivot bolt 

assembly. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Support for the NPRM 

Boeing supported the contents of the 

NPRM. 

Request To Include References to 

Airplane Maintenance Manual 

United Airlines (UAL) stated that it is 

concerned about the actions in Boeing 

Alert Service Bulletin 747–54A2232, 

dated April 15, 2010, being undone and 

leading to the same condition. UAL 

suggested that we revise the NPRM to 

include airplane maintenance manual 

(AMM) references, including a check for 

marker BAC27EPP667 before installing 

the access door. As an alternative, UAL 

also suggested that the mid-pivot access 

door part number could be changed 

instead of keeping the same part 

number. UAL stated that if the NPRM is 

not changed to incorporate one of the 

two options, then the required actions 

could be undone if doors without the 

marker are installed. 

We disagree with the request to revise 

this AD. Section 39.7 of the Federal 

Aviation Regulations (14 CFR 39.7) 

states the following: ‘‘Anyone who 

operates a product that does not meet 

the requirements of an applicable 

airworthiness directive is in violation of 

this section.’’ Therefore, operators are 

prohibited from installing a door that 

does not meet the requirements of this 

AD. However, operators are permitted to 

add a check to applicable AMM to 

prevent installing the incorrect access 

door. We have not changed the final 

rule in regard to this issue. 

Request To Clarify Figures in Service 

Information 

UPS requested that we clarify the 

figures C–C and D–D on sheets 7 and 8 

of Appendix B of Boeing Alert Service 

Bulletin 747–54A2232, dated April 15, 

2010. UPS stated that the transducer 


jlentini on DSKJ8SOYB1PROD with RULES
24350 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 

positions ‘A’ and ‘B’ on sheet 7 of 

Appendix B do not coincide with the 

transducer positions ‘A’ and ‘B’ on the 

cross-sections C and D on sheet 8 of 

Appendix B. 

We agree to clarify. Both sheets show 

the transducer in position ‘A’ over the 

grease channel, and the transducer in 

position ‘B’ adjacent to the grease 

channel. Sheet 7 provides a top-down 

view on the mid-pivot pin, and sheet 8 

is a side view with the grease channel 

in a single location for both views. The 

side view on sheet 8 is only intended to 

show which end of the pin is correct. 

No change to the service bulletin or rule 

is needed. We have not changed the 

final rule in regard to this issue. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Costs of Compliance 

We estimate that this AD affects 95 

airplanes of U.S. registry. We also 

estimate that it would take about 3 

work-hours per product to comply with 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD to the 

U.S. operators to be $24,225, or $255 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 

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 this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) 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. 

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 adding 

the following new airworthiness 

directive (AD): 

2011–09–14 The Boeing Company: 

Amendment 39–16676; Docket No. 

FAA–2010–1111; Directorate Identifier 

2010–NM–129–AD. 

Effective Date 

(a) This AD is effective June 6, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–200B, –300, –400, 

–400D, and –400F series airplanes; 

certificated in any category; equipped with 

Pratt and Whitney 4000 or General Electric 

CF6–80C2 series engines, as identified in 

Boeing Alert Service Bulletin 747–54A2232, 

dated April 15, 2010. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/pylons. 

Unsafe Condition 

(e) This AD was prompted by a report that 

the left and right access doors of the spring 

beam mid-pivot bolt assembly for the No. 1 

strut were inadvertently installed in the 

incorrect position during strut modification. 

The Federal Aviation Administration is 

issuing this AD to detect and correct 

incorrectly installed mid-pivot bolt 

assemblies on the spring beam on the 

outboard struts. Incorrectly installed bolt 

assemblies could lead to fatigue cracking and 

consequent fracturing of the mid-pivot bolt 

assembly, which could lead to loss of the 

spring beam load path and the possible 

separation of a strut and engine from the 

airplane during flight. 

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. 

Inspection To Determine if Correct Door Is 

Installed 

(g) Within 24 months after the effective 

date of this AD, do an inspection to 

determine if the correct mid-pivot access 

door is installed, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2232, dated April 

15, 2010. 

(h) If, during the inspection required by 

paragraph (g) of this AD, the correct midpivot door is found to be installed, before 

further flight, install a marker on the midpivot access door, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2232, dated April 

15, 2010. 

(i) If, during the inspection required by 

paragraph (g) of this AD, the correct midpivot door is not found to be installed, before 

further flight, do the actions required by 

paragraphs (i)(1), (i)(2), and (i)(3) of this AD, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2232, dated April 15, 2010. 

(1) Rotate the mid-pivot bolt assembly to 

the correct orientation and replace the midpivot access door with a new or serviceable 

mid-pivot access door. 

(2) Install a marker on the mid-pivot access 

door. 

(3) Do the actions required by paragraph 

(i)(3)(i) or (i)(3)(ii) of this AD. 

(i) (Option 1) Do an ultrasonic inspection 

for cracking of the mid-pivot bolt assembly. 

(A) If no cracking is found, do the actions 

required by paragraphs (i)(3)(i)(A)(1) and 

(i)(3)(i)(A)(2) of this AD. 

(1) Repeat the ultrasonic inspection for 

cracking of the mid-pivot bolt assembly 

thereafter at intervals not to exceed 24 

months until the action required by 

paragraph (i)(3)(i)(A)(2) of this AD is done. 

(2) Within 60 months after the effective 

date of this AD, replace the mid-pivot bolt 

assembly with a new mid-pivot bolt 

assembly. Replacement terminates the 

repetitive inspections required by paragraph 

(i)(3)(i)(A)(1) of this AD. 

(B) If any cracking is found, replace the 

mid-pivot bolt assembly with a new midpivot bolt assembly, before further flight. 

(ii) (Option 2) Replace the mid-pivot bolt 

assembly with a new mid-pivot bolt 

assembly. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 


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Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 24351 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle ACO 

to make those findings. For a repair method 

to be approved, the repair must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

Related Information 

(k) For more information about this AD, 

contact Kenneth Paoletti, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6434; fax (425) 917–6590; 

kenneth.paoletti@faa.gov. 

Material Incorporated by Reference 

(l) You must use Boeing Alert Service 

Bulletin 747–54A2232, dated April 15, 2010, 

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 

Boeing Alert Service Bulletin 747–54A2232, 

dated April 15, 2010, under 5 U.S.C. 552(a) 

and 1 CFR part 51. 

(2) 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. 

(3) You may review copies of the service 

information at the FAA, 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 an NARA facility, 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 April 15, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–9919 Filed 4–29–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0383; Directorate 

Identifier 2010–NM–093–AD; Amendment 

39–16675; AD 2011–09–13] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A340–200 and –300 Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 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: 

Further to accomplishment of A340 ALI 

tasks 545104, which require a rototest 

inspection as per Non Destructive Testing 

Manual (NTM) 54–51–04 of engine pylon 

pyramid attachment areas at aft end of lower 

arms between Rib 1 and Rib 2 (2 fastener 

locations/pylon), four findings have been 

reported and repaired. 

* * * * * 

The unsafe condition is cracking, which 

might impact the structural integrity of 

the airplane. This AD requires actions 

that are intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective May 

17, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 17, 2011. 

We must receive comments on this 

AD by June 16, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• 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 W12–40, 1200 New Jersey 

Avenue, SE., Washington, DC, between 

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

Friday, except Federal holidays. 

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 this AD, 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. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone: 

425–227–1138; fax: 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2008–0140, 

dated July 28, 2008 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Further to accomplishment of A340 ALI 

tasks 545104, which require a rototest 

inspection as per Non Destructive Testing 

Manual (NTM) 54–51–04 of engine pylon 

pyramid attachment areas at aft end of lower 

arms between Rib 1 and Rib 2 (2 fastener 

locations/pylon), four findings have been 

reported and repaired. 

Further investigations made on 

performances of High Frequency Eddy 

Current (HFEC) inspection techniques in 

steel led to the conclusion that existing NTM 

procedure 54–51–04 by rototest is not 

reliable because this method is not adapted 

to the ferromagnetic materials and therefore 

findings reported up to now using this 

procedure can be considered as uncertain. 

Therefore, a new inspection procedure 

using Ultra Sonic (US) testing without 

fastener removal has been developed. 

In order to comply with certification 

requirements, this Airworthiness Directive 

(AD) requires performing the new [repetitive] 

US inspection [for cracking] on all A340– 

200/–300 pre-modification 49203 

(reinforcements of pylon primary structure 

for enhanced A340). 


jlentini on DSKJ8SOYB1PROD with RULES