3150 Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0865; Directorate 

Identifier 2009–NM–023–AD; Amendment 

39–16168; AD 2010–01–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747SR, and 747SP 

Series Airplanes Equipped With 

General Electric CF6–45 or –50 Series 

Engines, or Equipped With Pratt & 

Whitney JT9D–3 or –7 (Excluding –70) 

Series Engines 

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– 

100, 747–100B, 747–100B SUD, 747– 

200B, 747–200C, 747–200F, 747–300, 

747SR, and 747SP series airplanes. That 

AD currently requires repetitive 

inspections to detect cracks and 

fractures of the strut front spar chord 

assembly (including the forward side) at 

each strut location, and repair if 

necessary. This new AD adds a one-time 

inspection for cracking of the forward 

side of the front spar chord assembly on 

the inboard and outboard struts, 

installation of a cap skin doubler for 

certain airplanes, and repair if 

necessary. These actions terminate the 

repetitive inspections of the forward 

side of the strut front spar chord 

assembly; the inspections of the aft side 

assembly continue as specified in the 

existing AD. This AD results from a 

report of a fractured front spar assembly 

for strut No. 3, which resulted in the 

loss of the strut upper link load path. 

We are issuing this AD to detect and 

correct cracks and fractures of the 

nacelle strut front spar chord assembly. 

Fracture of the front spar chord 

assembly could lead to loss of the strut 

upper link load path and consequent 

fracture of the diagonal brace, which 

could result in in-flight separation of the 

strut and engine from the airplane. 

DATES: This AD becomes effective 

February 24, 2010. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 24, 2010. 

On January 29, 2007 (72 FR 1427, 

January 12, 2007), the Director of the 

Federal Register approved the 

incorporation by reference of a certain 

other publication listed in the AD. 

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 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: Ken 

Paoletti, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6434; 

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 2007–01–15, amendment 

39–14887 (72 FR 1427, January 12, 

2007). The existing AD applies to 

certain Boeing Model 747–100, 747– 

100B, 747–100B SUD, 747–200B, 747– 

200C, 747–200F, 747–300, 747SR, and 

747SP series airplanes. That NPRM was 

published in the Federal Register on 

September 18, 2009 (74 FR 47897). That 

NPRM proposed to continue to require 

repetitive inspections to detect cracks 

and fractures of the strut front spar 

chord assembly (including the forward 

side) at each strut location, and repair 

if necessary. That NPRM also proposed 

to add a one-time inspection for 

cracking of the forward side of the front 

spar chord assembly on the inboard and 

outboard struts, installation of a cap 

skin doubler for certain airplanes, and 

repair if necessary. The additional 

actions proposed in that NPRM would 

terminate the repetitive inspections of 

the forward side of the strut front spar 

chord assembly; the inspections of the 

aft side assembly would continue as 

specified in the existing AD. 

Comments 

We provided the public the 

opportunity to participate in the 

development of this AD. We have 

considered the single comment received 

on the NPRM. Boeing concurs with the 

proposed requirements specified in the 

NPRM. 

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. 

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 (q)(3) 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 

program. 

Conclusion 

We have carefully reviewed the 

available data, including the comment 

that has 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. AD as proposed. 

Interim Action 

We consider the actions in this AD to 

be interim actions for the strut front spar 

chord assembly at each strut location, 

excluding the forward side (the 

terminating action for the forward side 

is included in this AD). If the 

manufacturer develops a modification 

for the remainder of the front spar chord 

assembly, we might consider additional 

rulemaking. 

Costs of Compliance 

There are about 411 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. 


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Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 3151 

ESTIMATED COSTS

Action Work hours Average labor 

rate per hour Parts Cost per airplane 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspections (required by AD 

2007-01-15).

17 ........................... $80 $0 ........................... $1,360, per inspection cycle.85 $115,600, per inspection cycle. 

One-time inspection 

and cap skin doubler installation 

(new action).

30 to 116 1 ............. $80 $893 to $36,737 1 .. $3,293 to $46,017 1 85 $279,905 to 

$3,911,445.1

1 Depending on airplane configuration. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this 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 39–14887 (72 

FR 1427, January 12, 2007) and by 

adding the following new airworthiness 

directive (AD): 

2010–01–10 The Boeing Company: 

Amendment 39–16168. Docket No. 

FAA–2009–0865; Directorate Identifier 

2009–NM–023–AD. 

Effective Date 

(a) This AD becomes effective February 24, 

2010. 

Affected ADs 

(b) This AD supersedes AD 2007–01–15, 

Amendment 39–14887. 

Applicability 

(c) This AD applies to The Boeing 

Company Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–200F, 

747–300, 747SR, and 747SP series airplanes, 

certificated in any category, equipped with 

General Electric CF6–45 or -50 series engines, 

or equipped with Pratt & Whitney JT9D–3 or 

-7 (excluding -70) series engines, as 

identified in Boeing Alert Service Bulletin 

747–54A2224, Revision 1, dated November 

16, 2006. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 54: Nacelles/Pylons. 

Unsafe Condition 

(e) This AD results from a report of a 

fractured front spar assembly for strut No. 3, 

which resulted in the loss of the strut upper 

link load path. The Federal Aviation 

Administration is issuing this AD to detect 

and correct cracks and fractures of the 

nacelle strut front spar chord assembly. 

Fracture of the front spar chord assembly 

could lead to loss of the strut upper link load 

path and consequent fracture of the diagonal 

brace, which could result in in-flight 

separation of the strut and engine from 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 2004– 

25–05, Amendment 39–13893 

Aft Side Detailed and High Frequency Eddy 

Current (HFEC) Inspections With New 

Service Information 

(g) Within 90 days after December 27, 2004 

(the effective date of AD 2004–25–05, which 

was superseded by AD 2007–01–15), perform 

detailed and HFEC inspections to detect any 

cracks or fractures of the front spar chord 

assembly for strut numbers 1 through 4 

inclusive, in accordance with Boeing Alert 

Service Bulletin 747–54A2224, dated 

September 30, 2004; or in accordance with 

Part 1—Aft Side Inspection of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–54A2224, Revision 1, 

dated November 16, 2006. As of January 29, 

2007 (the effective date of AD 2007–01–15), 

only Part 1—Aft Side Inspection of the 

Accomplishment Instructions of Revision 1 

of Boeing Alert Service Bulletin 747– 

54A2224, Revision 1, dated November 16, 

2006, may be used. 

(h) Accomplishment of the detailed and 

HFEC inspections in accordance with Boeing 

747 Fleet Team Digest 747–FTD–54–04002, 

dated April 15, 2004, May 4, 2004, June 1, 

2004, July 12, 2004, or July 28, 2004; or 

Boeing Message 1–C6ELC (Service Request ID 

No.: 218724992), dated April 14, 2004; before 

December 27, 2004, is considered acceptable 

for compliance with the requirements of 

paragraph (g) of this AD. 

Repetitive Inspections 

(i) For airplanes on which no crack or 

fracture is detected during the inspections 


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3152 Federal Register / Vol. 75, No. 12 / Wednesday, January 20, 2010 / Rules and Regulations 

required by paragraph (g) of this AD: At the 

applicable times specified in Table 1— 

Repetitive Intervals of this AD, repeat the 

detailed and HFEC inspections required by 

paragraph (g) of this AD. 

TABLE 1—REPETITIVE INTERVALS

For airplanes identified in Boeing Alert Service Bulletin 747-54A2224, dated 

September 30, 2004; or Revision 1, dated November 16, 2006; as— Repeat the inspections at intervals not to exceed— 

Group 1 ............................................................................................................................ 1,000 flight cycles or 18 months, whichever occurs first. 

Group 2 and Group 3 ...................................................................................................... 1,200 flight cycles or 18 months, whichever occurs first. 

Group 4 and Group 6 ...................................................................................................... 1,500 flight cycles or 18 months, whichever occurs first. 

Group 5 ............................................................................................................................ 2,000 flight cycles or 18 months, whichever occurs first. 

Corrective Action 

(j) If any crack or fracture is found during 

any inspection required by paragraphs (g) 

and (i) of this AD, and Boeing Alert Service 

Bulletin 747–54A2224, dated September 30, 

2004; or Revision 1, dated November 16, 

2006; specifies contacting Boeing for 

appropriate action: Before further flight, 

repair the crack or fracture using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. 

Restatement of Requirements of AD 2007– 

01–15 

Forward Side Detailed and HFEC 

Inspections 

(k) Within 90 days after January 29, 2007 

the effective date of AD 2007–01–15), do 

detailed and HFEC inspections for any cracks 

or fracture of the front spar chord assembly 

for strut numbers 1, 2, 3, and 4, in 

accordance with Part 2—Forward Side 

Inspection of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2224, Revision 1, dated November 

16, 2006. If no crack or fracture is found, 

repeat the inspections thereafter at the 

applicable interval specified in Table 1 of 

this AD. Doing the inspections required by 

paragraph (n) of this AD terminates the 

forward side detailed and HFEC inspection 

requirements of this paragraph. 

Corrective Action for Forward Side 

Inspection 

(l) If any crack or fracture is found during 

any inspection required by paragraph (k) of 

this AD, and Boeing Alert Service Bulletin 

747–54A2224, Revision 1, dated November 

16, 2006, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair the crack or fracture using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. 

Credit for Inspections Done According to 

Boeing 747 Fleet Team Digest 

(m) Detailed and HFEC inspections done 

before January 29, 2007, in accordance with 

Boeing 747 Fleet Team Digest 747–FTD–54– 

06002, dated June 29, 2006; or October 16, 

2006; are acceptable for compliance with the 

initial inspection required by paragraph (k) of 

this AD. 

New Requirements of This AD 

Inspection and Corrective Actions 

(n) At the applicable time specified in 

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

Service Bulletin 747–54A2230, dated October 

30, 2008; except that where the service 

bulletin specifies a compliance time after the 

date on the service bulletin, this AD requires 

compliance within the specified compliance 

time after the effective date of this AD: Do 

an open-hole high frequency eddy current 

(HFEC) inspection for cracking of the forward 

side of the front spar chord assembly on the 

inboard and outboard struts; and, for 

airplanes on which the cap skin doubler is 

not installed, install the cap skin doubler; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–54A2230, dated October 30, 2008. 

(o) If any crack is found during the 

inspection required by paragraph (n) of this 

AD: Before further flight, repair the crack 

using a method approved in accordance with 

the procedures specified in paragraph (q) of 

this AD. 

(p) Doing all applicable actions required by 

paragraphs (n) and (o) of this AD terminates 

the repetitive forward side detailed and 

HFEC inspection requirements of paragraph 

(k) of this AD. All aft side inspection 

requirements of this AD remain in effect. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(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: Ken 

Paoletti, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6434; fax (425) 917–6590. Or, email 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) 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. 

(4) AMOCs approved previously in 

accordance with AD 2007–01–15 are 

approved as AMOCs for the corresponding 

provisions of this AD. 

Material Incorporated by Reference 

(r) You must use Boeing Alert Service 

Bulletin 747–54A2224, Revision 1, dated 

November 16, 2006; and Boeing Alert Service 

Bulletin 747–54A2230, dated October 30, 

2008; as applicable; 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 747–54A2230, 

dated October 30, 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 Boeing Alert Service Bulletin 

747–54A2224, Revision 1, dated November 

16, 2006, on January 29, 2007 (72 FR 1427, 

January 12, 2007). 

(3) 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. 

(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 or 425–227–1152. 

(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 30, 2009. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–31363 Filed 1–19–10; 8:45 am] 

BILLING CODE 4910–13–P 


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