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within 10 days after the effective date of this 

AD. 

Parts Installation 

(l) For all airplanes: As of the effective date 

of this AD, no person may install an elevator 

tab control mechanism, part number 

251A2430–( ), on any airplane, unless the 

mechanism has been inspected before and 

after installation, in accordance with the 

requirements of paragraph (g) of this AD, and 

no discrepancies have been found. 

Special Flight Permit 

(m) Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed. 

Alternative Methods of Compliance 

(AMOCs) 

(n)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), 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: Kelly 

McGuckin, Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 425– 

917–6490; fax 425–917–6590. Information 

may be e-mailed to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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 refer to this AD. 

(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. 

Material Incorporated by Reference 

(o) You must use Boeing Alert Service 

Bulletin 737–27A1296, dated March 12, 

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 

this service information 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, 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 March 

18, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6786 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0684; Directorate 

Identifier 2008–NM–149–AD; Amendment 

39–16247; AD 2010–07–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–200C and –200F 

Series Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD), 

which applies to certain Model 747– 

200C and –200F series airplanes. That 

AD currently requires repetitive 

inspections to find fatigue cracking in 

the floor panel attachment fastener 

holes of the upper chord of certain 

upper deck floor beams in Section 41 

(i.e., body station 520 and forward), and 

repair if necessary. The existing AD also 

provides optional modifications, which 

extend the threshold for initiating 

certain repetitive inspections. This new 

AD requires additional repetitive 

inspections to find fatigue cracking in 

the floor panel attachment fastener 

holes of the upper chord of certain other 

upper deck floor beams in Section 41 

and Section 42 (i.e., aft of body station 

520); repetitive inspections to find 

fatigue cracking in the permanent 

fastener holes of the upper chord of 

certain upper deck floor beams in 

Section 41; and related investigative and 

corrective actions. This new AD also 

provides a new optional modification, 

which terminates certain repetitive 

inspections. This AD results from new 

reports of cracking in the upper chord 

of the upper deck floor beams in 

Sections 41 and 42, and new analysis 

that shows the permanent fastener holes 

of the upper chord of certain upper deck 

floor beams in Section 41 are also 

susceptible to fatigue cracking. We are 

issuing this AD to detect and correct 

cracking in the upper chord of the upper 

deck floor beams. Such cracking could 

extend and sever the floor beams, which 

could result in rapid decompression and 

loss of controllability of the airplane. 

DATES: This AD becomes effective May 

7, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 7, 2010. 

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. 

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 (telephone 800–647–5527) 

is the Docket 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: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6437; 

fax (425) 917–6590. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The FAA issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that 

supersedes AD 2006–08–02, amendment 

39–14556 (70 FR 18618, April 12, 2006). 

The existing AD applies to certain 

Model 747–200C and –200F series 

airplanes. That NPRM was published in 

the Federal Register on August 12, 2009 

(74 FR 40529). That NPRM proposed to 

continue to require repetitive 

inspections to find fatigue cracking in 

the floor panel attachment fastener 


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holes of the upper chord of certain 

upper deck floor beams in Section 41 

(i.e., body station 520 and forward), and 

repair if necessary. That NPRM also 

proposed to continue to provide 

optional modifications, which extend 

the threshold for the initiation of certain 

repetitive inspections. That NPRM also 

proposed to add repetitive inspections 

to find fatigue cracking in the floor 

panel attachment fastener holes of the 

upper chord of certain other upper deck 

floor beams in Section 41 and Section 

42 (i.e., aft of body station 520); 

repetitive inspections to find fatigue 

cracking in the permanent fastener holes 

of the upper chord of certain upper deck 

floor beams in Section 41; and related 

investigative and corrective actions. 

Additionally, that NPRM proposed to 

provide a new optional modification, 

which would terminate certain 

repetitive inspections. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the comments that have 

been received on the NPRM from the 

single commenter. 

Request To Revise Procedure Location 

Specified in Step (5) of Table 2 of the 

NPRM 

Boeing requests that we revise Table 

2 of the NPRM to update the location in 

the referenced service bulletin for the 

modification provided in Step (5) of 

Table 2 of the NPRM. Boeing points out 

that the modification referred to in 

paragraph (h)(2) of AD 2006–08–02, 

provided in Step (5) in Table 2 of the 

NPRM, was defined in Figure 5 of the 

original issue of Boeing Alert Service 

Bulletin 747–53A2439, dated July 5, 

2001. Boeing further points out that the 

instructions for this modification were 

moved to Part 3 and Part 4 of the Work 

Instructions of Revision 2, dated July 17, 

2008, of Boeing Alert Service Bulletin 

747–53A2439. 

We do not agree to revise Table 2 of 

this AD. Step (5) of Table 2 references 

paragraph (i)(2) of this AD, and requires 

only the fastener hole modification per 

Figure 5 and the open-hole highfrequency eddy current (HFEC) 

inspection per Part 1 of the Work 

Instructions of Boeing Alert Service 

Bulletin 747–53A2439, Revision 2, 

dated July 17, 2008. The fastener hole 

slot repair per Part 4 of the Work 

Instructions of Boeing Alert Service 

Bulletin 747–53A2439, Revision 2, 

dated July 17, 2008, is not required by 

paragraph (i)(2) of this AD. We note that 

the fastener hole slot repair per Part 4 

of the Work Instructions of Boeing Alert 

Service Bulletin 747–53A2439, Revision 

2, dated July 17, 2008, which is 

referenced in Part 2 of the Work 

Instructions of Boeing Alert Service 

Bulletin 747–53A2439, Revision 2, 

dated July 17, 2008, is required by 

paragraph (i)(1) of this AD. We have 

made no change to the final rule in this 

regard. 

Request To Update Name of Boeing’s 

Delegation Option Authorization 

Organization 

Boeing requests that we revise 

paragraphs (h)(1) and (o)(4) of the 

NPRM to change ‘‘Boeing Commercial 

Airplanes Delegation Option 

Authorization Organization’’ to ‘‘Boeing 

Commercial Airplanes Organization 

Designation Authorization 

Organization.’’ Boeing points out that 

they changed the name of this 

organization at the end of August 2009. 

We partially agree. Boeing 

Commercial Airplanes has received an 

Organization Designation Authorization 

(ODA), which replaces their previous 

designation as a Delegation Option 

Authorization holder. We have revised 

paragraph (o)(4) of this AD to delegate 

the authority to approve an alternative 

method of compliance for any repair 

required by this AD to the Boeing 

Commercial Airplanes ODA rather than 

an Authorized Representative under the 

former Delegation Option Authorization 

(DOA) program. However, we have also 

revised paragraph (h)(1) of this AD to 

reference paragraph (o) of this AD and 

to continue to provide allowance for 

those operators that have used a repair 

approved by a Boeing Company 

Designated Engineering Representative 

(DER) or by an Authorized 

Representative for the Boeing 

Commercial Airplanes DOA. 

Explanation of Changes Made to This 

AD 

We have revised this AD to identify 

the legal name of the manufacturer as 

published in the most recent type 

certificate data sheet for the affected 

airplane models. 

Conclusion 

We have carefully reviewed the 

available data, including the comments 

that have been received, and determined 

that air safety and the public interest 

require adopting the AD with the 

changes described previously. We have 

determined that these changes will 

neither increase the economic burden 

on any operator nor increase the scope 

of the AD. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the original NPRM, 

we have increased the labor rate used in 

the Costs of Compliance from $80 per 

work-hour to $85 per work-hour. The 

Costs of Compliance information, 

below, reflects this increase in the 

specified hourly labor rate. 

Costs of Compliance 

There are about 68 airplanes of the 

affected design in the worldwide fleet. 

The following table provides the 

estimated costs for U.S. operators to 

comply with this AD. 

ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspections (required by AD 

2006–08–02).

29 $85 $2,465 per inspection cycle .... 25 $61,625 per inspection cycle. 

Inspection of Area 5 and permanent fastener hole in 

Areas 1, 2, 3, and 4 (new required action).

78 85 $6,630 per inspection cycle .... 25 $165,750 per inspection cycle. 

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. 


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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 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); 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. 

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, 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 Federal Aviation 

Administration (FAA) amends § 39.13 

by removing amendment 39–14556 (70 

FR 18618, April 12, 2006) and by adding 

the following new airworthiness 

directive (AD): 

2010–07–03 The Boeing Company: 

Amendment 39–16247. Docket No. 

FAA–2009–0684; Directorate Identifier 

2008–NM–149–AD. 

Effective Date 

(a) This AD becomes effective May 7, 2010. 

Affected ADs 

(b) This AD supersedes AD 2006–08–02, 

Amendment 39–14556. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–200C and –200F series 

airplanes, certificated in any category, as 

identified in Boeing Alert Service Bulletin 

747–53A2439, Revision 2, dated July 17, 

2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from new reports of 

cracking in the upper chord of the upper 

deck floor beams in Sections 41 and 42, and 

new analysis that shows the permanent 

fastener holes of the upper chord of certain 

upper deck floor beams in Section 41 are also 

susceptible to fatigue cracking. We are 

issuing this AD to detect and correct cracking 

in the upper chord of the upper deck floor 

beams. Such cracking could extend and sever 

the floor beams, which could result in rapid 

decompression and loss of controllability 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. 

Requirements of AD 2006–08–02 

Initial Compliance Time at a New Reduced 

Threshold 

(g) At the earliest of the times specified in 

paragraphs (g)(1) through (g)(3) of this AD, do 

the inspection required by paragraph (h) of 

this AD. 

(1) Before the accumulation of 22,000 total 

flight cycles, or within 1,000 flight cycles 

after March 15, 2004 (the effective date of AD 

2004–03–11, which was superseded by AD 

2006–08–02), whichever occurs later. 

(2) For airplanes with 17,000 or more total 

flight cycles as of May 17, 2006 (the effective 

date of AD 2006–08–02): Before the 

accumulation of 18,000 total flight cycles, or 

within 90 days after May 17, 2006, whichever 

occurs later. 

(3) For airplanes with fewer than 17,000 

total flight cycles as of May 17, 2006: Before 

the accumulation of 15,000 total flight cycles, 

or within 1,000 flight cycles after May 17, 

2006, whichever occurs later. 

Inspections at Reduced Intervals for Certain 

Floor Beams and Repair 

(h) Do the applicable inspection to find 

fatigue cracking in the upper chord of the 

upper deck floor beams as specified in Part 

1 (Open-Hole High Frequency Eddy Current 

(HFEC) Inspection Method) or Part 2 (Surface 

HFEC Inspection Method) of the Work 

Instructions of Boeing Alert Service Bulletin 

747–53A2439, dated July 5, 2001. Do the 

inspections per the Boeing Alert Service 

Bulletin 747–53A2439, dated July 5, 2001, 

except as provided by paragraph (k) of this 

AD. Any combination of the applicable 

inspection methods specified in Parts 1 and 

2 may be used, provided that the 

corresponding repetitive inspection interval 

is used. 

(1) If any crack is found, before further 

flight, repair per Part 3 (Upper Chord Repair) 

of the Work Instructions of Boeing Alert 

Service Bulletin 747–53A2439, dated July 5, 

2001; except where Boeing Alert Service 

Bulletin 747–53A2439, dated July 5, 2001, 

specifies to contact Boeing for appropriate 

action, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (o) of this 

AD or repair according to data meeting the 

certification basis of the airplane approved 

by a Boeing Company Designated 

Engineering Representative (DER) or by an 

Authorized Representative for the Boeing 

Commercial Airplanes Delegation Option 

Authorization Organization. For a repair 

method to be approved by the Manager, 

Seattle Aircraft Certification Office (ACO), 

FAA, as required by this paragraph, the 

Manager’s approval letter must specifically 

reference this AD. Do the applicable 

inspection of the repaired area per Part 1 of 

the Work Instructions of Boeing Alert Service 

Bulletin 747–53A2439, dated July 5, 2001, at 

the applicable time per Part 3 of the Work 

Instructions of Boeing Alert Service Bulletin 

747–53A2439, dated July 5, 2001, and repeat 

the applicable inspection at the applicable 

interval per Figure 1 of Boeing Alert Service 

Bulletin 747–53A2439, dated July 5, 2001. 

(2) If no crack is found, repeat the 

applicable inspection per paragraph (h) of 

this AD at the applicable time specified in 

paragraphs (h)(2)(i) through (h)(2)(iii) of this 

AD. As an option to the repetitive 

inspections, accomplishment of paragraph 

(i)(1) or (i)(2) of this AD, before further flight, 

extends the threshold for the initiation of the 

repetitive inspections required by this 

paragraph. 

(i) If the immediately preceding inspection 

was conducted using an open-hole HFEC 

inspection method: Conduct the next 

inspection of that area within 3,000 flight 

cycles of the last inspection. 

(ii) If the immediately preceding inspection 

was conducted using a surface HFEC 

inspection method at stations 340 through 

420 inclusive and station 500: Conduct the 

next inspection of that area within 750 flight 

cycles of the last inspection. 

(iii) If the immediately preceding 

inspection was conducted using a surface 

HFEC inspection method at stations 440 and 

520: Conduct the next inspection of that area 

at the earlier of the times specified in 

paragraphs (h)(2)(iii)(A) and (h)(2)(iii)(B) of 

this AD, and thereafter at intervals not to 

exceed 250 flight cycles. 

(A) Within 750 flight cycles since the last 

surface HFEC inspection required by 

paragraph (h) of this AD. 

(B) Within 250 flight cycles after May 17, 

2006. 


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Optional Repair/Modification 

(i) For areas on which the inspection 

required by paragraph (h) of this AD is done 

per Part 1 of the Work Instructions of Boeing 

Alert Service Bulletin 747–53A2439, dated 

July 5, 2001; and on which no cracking is 

found: Accomplishment of the actions 

specified in either paragraph (i)(1) or (i)(2) of 

this AD extends the threshold for the 

initiation of the repetitive inspections 

required by paragraph (h)(2) of this AD. For 

areas on which the inspection required by 

paragraph (h) of this AD is done per Part 2 

of Boeing Alert Service Bulletin 747– 

53A2439, dated July 5, 2001; and on which 

no cracking is found: Accomplishment of the 

actions specified in paragraph (i)(1) of this 

AD extends the threshold for the initiation of 

the repetitive inspections required by 

paragraph (h)(2) of this AD. 

(1) Do the applicable repair per Part 3 of 

the Work Instructions of Boeing Alert Service 

Bulletin 747–53A2439, dated July 5, 2001, 

except as provided by paragraph (k) of this 

AD. At the applicable time specified in Table 

1 of Part 3 of the Work Instructions of Boeing 

Alert Service Bulletin 747–53A2439, dated 

July 5, 2001, do the applicable inspection of 

the repaired area per Part 1 of the Work 

Instructions of Boeing Alert Service Bulletin 

747–53A2439, dated July 5, 2001. Repeat the 

inspection thereafter within the applicable 

interval of 3,000 flight cycles per Figure 1 of 

Boeing Alert Service Bulletin 747–53A2439, 

dated July 5, 2001. 

(2) Do the modification of the attachment 

hole of the floor panel per Figure 5 of Boeing 

Alert Service Bulletin 747–53A2439, dated 

July 5, 2001, except as provided by paragraph 

(k) of this AD. Within 10,000 flight cycles 

after accomplishment of the modification, do 

the inspection of the modified area per Part 

1 of the Work Instructions of Boeing Alert 

Service Bulletin 747–53A2439, dated July 5, 

2001. Repeat the inspection thereafter within 

the applicable interval of 3,000 flight cycles 

per Figure 1 of Boeing Alert Service Bulletin 

747–53A2439, dated July 5, 2001. 

Determining the Number of Flight Cycles for 

Compliance Time 

(j) For the purposes of calculating the 

compliance threshold and repetitive intervals 

for actions required by paragraph (g), (h), or 

(i) of this AD: As of May 17, 2006 (the 

effective date of AD 2006–08–02), all flight 

cycles, including the number of flight cycles 

in which cabin differential pressure is at 2.0 

pounds per square inch (psi) or less, must be 

counted when determining the number of 

flight cycles that have occurred on the 

airplane. 

New Requirements of This AD 

Applicable Revisions of Service Bulletins 

(k) Use the information in Tables 1 and 2 

of this AD, at the applicable time specified 

in paragraphs (k)(1) and (k)(2) of this AD, to 

determine the part of the applicable service 

bulletin to use to accomplish the actions 

required by this AD. 

(1) On or after May 17, 2006, but before the 

effective date of this AD, use only the service 

information listed in Table 1 or Table 2 of 

this AD. 

TABLE 1—SERVICE INFORMATION GIVEN IN BOEING ALERT SERVICE BULLETIN 747–53A2439, REVISION 1, DATED MARCH

10, 2005 

Do— In accordance with— 

(1) The actions required by paragraph (h) of 

this AD.

Parts 1 and 2 of the Work Instructions of Boeing Alert Service Bulletin 747–53A2439, Revision 

1, dated March 10, 2005; as applicable. 

(2) The applicable inspection of the repaired 

area required by paragraph (h)(1) of this AD.

Parts 1 and 6 of the Work Instructions of Boeing Alert Service Bulletin 747–53A2439, Revision 

1, dated March 10, 2005; as applicable; at the applicable time specified in Table 1 of Part 3 

of the Work Instructions of that service bulletin. 

(3) The actions required by paragraph (i)(1) of 

this AD.

Parts 1, 3, and 6 of the Work Instructions of Boeing Alert Service Bulletin 747–53A2439, Revision 1, dated March 10, 2005; as applicable. 

(4) The actions required by paragraph (i)(2) of 

this AD.

Figure 5 and Part 1 of the Work Instructions of Boeing Alert Service Bulletin 747–53A2439, 

Revision 1, dated March 10, 2005; as applicable. 

(2) On or after the effective date of this AD, 

use only the service information listed in 

Table 2 of this AD. 

TABLE 2—SERVICE INFORMATION GIVEN IN BOEING ALERT SERVICE BULLETIN 747–53A2439, REVISION 2, DATED JULY

17, 2008 

Do— In accordance with— 

(1) The actions required by paragraph (h) and 

(l) of this AD.

Part 1 (open-hole or surface HFEC inspection, as applicable) of the Work Instructions of Boeing Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008. 

(2) The applicable inspection of the repaired 

area required by paragraph (h)(1) of this AD.

Part 1 (open-hole HFEC inspection only) and Part 5 of the Work Instructions of Boeing Alert 

Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008; at the applicable time specified in Table 1 of Part 2 of the Work Instructions of that service bulletin. 

(3) The applicable repair required by paragraph 

(h)(1) of this AD.

Part 2 (upper chord repair at floor panel attach holes) of the Work Instructions of Boeing Alert 

Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008. 

(4) The actions required by paragraph (i)(1) of 

this AD.

Part 1 (open-hole HFEC inspection only), Part 2, and Part 5 of the Work Instructions of Boeing 

Alert Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008. 

(5) The actions required by paragraph (i)(2) of 

this AD.

Figure 5 and Part 1 (open-hole HFEC inspection only) of the Work Instructions of Boeing Alert 

Service Bulletin 747–53A2439, Revision 2, dated July 17, 2008. 

New Inspections and Related Investigative 

and Corrective Actions 

(l) For all airplanes, except as provided by 

paragraphs (k)(1) and (k)(2) of this AD: At the 

applicable time specified in Paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2439, Revision 2, dated July 

17, 2008, do the applicable open-hole or 

surface HFEC inspections for fatigue cracking 

in the upper chord of the upper deck floor 

beams in Area 5, and the inspection for 

fatigue cracking in the permanent fastener 

holes of the upper chord of certain upper 

deck floor beams in Areas 1, 2, 3, and 4, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2439, Revision 2, dated July 17, 

2008. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the applicable inspection thereafter at 

the applicable interval specified in Paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2439, Revision 2, dated July 

17, 2008. 


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(1) Where Boeing Alert Service Bulletin 

747–53A2439, Revision 2, dated July 17, 

2008, specifies a compliance time relative to 

the date of issuance of that service bulletin, 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2439, Revision 2, dated July 17, 

2008, specifies contacting Boeing for repair 

data: Before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (o) of this 

AD. 

Optional New Modification for Areas 1, 2, 3, 

and 4 

(m) For areas 1, 2, 3, and 4 as defined in 

Boeing Alert Service Bulletin 747–53A2439, 

Revision 2, dated July 17, 2008: Doing the 

modification and post-modification actions 

specified in Boeing Alert Service Bulletin 

747–53A2696, dated October 16, 2008, 

terminates the repetitive inspection 

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

AD. Doing the modification and postmodification actions specified in Boeing 

Alert Service Bulletin 747–53A2696, dated 

October 16, 2008, terminates the repetitive 

inspection requirements of paragraph (l) of 

this AD, except at the upper deck floor beam 

at body station (BS) 460 and 480 and the 

upper deck floor beams aft of BS 520. 

No Reporting Requirement 

(n) Although Boeing Alert Service Bulletin 

747–53A2439, Revision 1, dated March 10, 

2005; and Boeing Alert Service Bulletin 747– 

53A2439, Revision 2, dated July 17, 2008; 

specify to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

Alternative Methods of Compliance 

(AMOCs) 

(o)(1) The Manager, Seattle ACO, 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: Ivan 

Li, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6437; fax (425) 917–6590. Or, 

e-mail information to 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. 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. 

(3) AMOCs approved previously in 

accordance with AD 2006–08–02, are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(4) 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. 

Material Incorporated by Reference 

(p) You must use Boeing Alert Service 

Bulletin 747–53A2439, Revision 2, dated July 

17, 2008, to do the actions required by this 

AD, unless the AD specifies otherwise. If you 

accomplish the new optional actions 

specified by this AD, you must use Boeing 

Alert Service Bulletin 747–53A2696, dated 

October 16, 2008, to perform those actions, 

unless the AD specifies otherwise. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information 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, 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 March 

17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–6546 Filed 4–1–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2005–19559; Directorate 

Identifier 2004–NE–03–AD; Amendment 39– 

16254; AD 2010–07–09] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc RB211–Trent 700 Series Turbofan 

Engines 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

Rolls-Royce plc RB211–Trent 700 series 

turbofan engines. That AD currently 

requires initial and repetitive borescope 

inspections of the high-pressure-andintermediate pressure (HP–IP) turbine 

internal and external oil vent tubes for 

coking and carbon buildup, and 

cleaning or replacing the vent tubes if 

necessary. This AD requires the same 

actions, but adds additional inspections 

of the vent flow restrictor. This AD 

results from further analysis that the 

cleaning of the vent tubes required by 

AD 2007–02–05 could lead to loosened 

carbon fragments, causing a blockage 

downstream in the vent flow restrictor. 

We are issuing this AD to prevent 

internal oil fires due to coking and 

carbon buildup that could cause 

uncontained engine failure and damage 

to the airplane. 

DATES: This AD becomes effective May 

7, 2010. The Director of the Federal 

Register approved the incorporation by 

reference of certain publications listed 

in the regulations as of May 7, 2010. 

ADDRESSES: You can get the service 

information identified in this AD from 

Rolls-Royce plc, P.O. Box 31, Derby, 

England; telephone: 011–44–1332– 

249428; fax: 011–44–1332–249223. 

The Docket Operations office is 

located at Docket Management Facility, 

U.S. Department of Transportation, 1200 

New Jersey Avenue, SE., West Building 

Ground Floor, Room W12–140, 

Washington, DC 20590–0001. 

FOR FURTHER INFORMATION CONTACT: 

James Lawrence, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

and Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: james.lawrence@faa.gov; 

telephone (781) 238–7176; fax (781) 

238–7199. 

SUPPLEMENTARY INFORMATION: The FAA 

proposed to amend 14 CFR part 39 by 

superseding AD 2007–02–05, 

Amendment 39–14892 (72 FR 2603, 

January 22, 2007), with a proposed AD. 

The proposed AD applies to Rolls-Royce 

plc RB211–Trent 700 series turbofan 

engines. We published the proposed AD 

in the Federal Register on October 26, 

2009 (74 FR 54940). That action 

proposed to require initial and 

repetitive borescope inspections of the 

HP–IP turbine internal and external oil 

vent tubes for coking and carbon 

buildup, cleaning or replacing the vent 

tubes if necessary, and inspections of 

the vent flow restrictor. 

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, 


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