81430 Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 

Alternative Methods of Compliance 

(AMOCs) 

(o)(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: 

Nicholas Han, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle ACO, 1601 

Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6449; fax 

(425) 917–6590. Information may be e-mailed 

to: 9-ANM-Seattle-ACO-AMOCRequests@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) or other 

person 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 2006–05–09 are 

approved as alternative methods of 

compliance with the corresponding 

requirements of this AD. 

Material Incorporated by Reference 

(p) You must use Boeing Alert Service 

Bulletin 747–53A2499, dated August 11, 

2005; or Boeing Service Bulletin 747– 

53A2499, Revision 2, dated August 12, 2010; 

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 Service Bulletin 747–53A2499, 

Revision 2, dated August 12, 2010, 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 

747–53A2499, dated August 11, 2005, on 

April 13, 2006 (71 FR 12122, March 9, 2006). 

(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. 

(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 13, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–31992 Filed 12–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0674; Directorate 

Identifier 2010–NM–012–AD; Amendment 

39–16546; AD 2010–26–07] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model 747 Airplanes 

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 

repetitive inspections for cracking in the 

body skin around the aft corners of the 

nose wheel well; for certain airplanes, 

repetitive inspections for cracking in the 

skin splice plate at the aft corners of the 

nose wheel well; and related 

investigative and corrective actions if 

necessary. This AD also requires 

repetitive post-modification inspections 

for cracking in the body skin and the 

skin splice plate; for certain airplanes, 

an inspection for steel cross-shaped 

doublers on the larger aluminum 

doublers; and corrective action if 

necessary. This AD also requires 

repetitive surface high frequency eddy 

current (HFEC) inspections of a certain 

bulkhead outer chord, skin splice plate, 

and outer chord radius filler for 

cracking; repetitive detailed inspections 

for cracking of the bulkhead frame web 

and body skin; and corrective actions if 

necessary. This AD provides for 

optional terminating action for certain 

repetitive inspections. This AD was 

prompted by reports of cracking of the 

fuselage skin and adjacent internal skin 

splice plate at the left and right nose 

wheel well aft corners, and the outer 

chord of the body station (BS) 400 

bulkhead. We are issuing this AD to 

detect and correct cracking of the 

fuselage skin or splice plate, which, 

together with cracking of the bulkhead 

outer chord, could result in large skin 

cracks and subsequent in-flight rapid 

decompression of the airplane. 

DATES: This AD is effective February 1, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 1, 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: 

Steven Fox, Senior Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone 

(425) 917–6425; fax (425) 917–6590; email: steven.fox@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 

July 8, 2010 (75 FR 39189). That NPRM 

proposed to require repetitive 

inspections for cracking in the body 

skin around the aft corners of the nose 

wheel well; for certain airplanes, 

repetitive inspections for cracking in the 

skin splice plate at the aft corners of the 

nose wheel well; and related 

investigative and corrective actions if 


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Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 81431 

necessary. The NPRM also proposed to 

require repetitive post-modification 

inspections for cracking in the body 

skin and the skin splice plate; for 

certain airplanes, an inspection for steel 

cross-shaped doublers on the larger 

aluminum doublers; and corrective 

action if necessary. The NPRM also 

proposed to require repetitive surface 

high frequency eddy current (HFEC) 

inspections of a certain bulkhead outer 

chord, skin splice plate, and outer chord 

radius filler for cracking; repetitive 

detailed inspections for cracking of the 

bulkhead frame web and body skin; and 

corrective actions if necessary. That 

NPRM also proposed to provide for 

optional terminating action for certain 

repetitive inspections. 

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. 

Request To Revise Paragraph (r) of the 

NPRM 

Boeing requested that we revise 

paragraph (r) of the NPRM to note that 

the threshold of the initial inspection, in 

accordance with Boeing Document No. 

D6–35022, Volumes 1 and 2 

‘‘Supplemental Structural Inspection 

Document (SSID) for Model 747 

Airplanes,’’ Revision G, dated December 

2000, Item F–4, remains as given in AD 

2004–07–22 R1 (73 FR 1052, January 7, 

2008) (A correction to AD 2004–07–22 

R1 was published in the Federal 

Register on February 14, 2008 (73 FR 

8589)). Boeing stated that while the 

inspection method and intervals 

provided in Boeing Alert Service 

Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009, are alternative 

methods of compliance (AMOCs) to 

Revision G of the Model 747 SSID, Item 

F–4, the requirement to comply with the 

SSID inspection threshold remains as 

given in AD 2004–07–22 R1. 

We disagree with the request to revise 

paragraph (r) of this AD to include the 

requested notation. Paragraph (r) of this 

AD does not provide any indication of 

change to the initial inspection 

threshold for the initial inspection 

according to Revision G of the Model 

747 SSID, Item F–4. As the commenter 

stated, the inspection threshold for Item 

F–4 remains as given in AD 2004–07– 

22 R1. Paragraph (b) of this AD also 

indicates that no other AD is affected by 

this AD. No change has been made to 

the AD in this regard. 

Request To Include Alternative 

Inspection Procedures as AMOCs or To 

Extend the Grace Period 

Japan Airlines (JAL) requested 

approval of an AMOC for inspections 

for airplanes that have been previously 

repaired. JAL stated that 14 of its Model 

747–400 airplanes have had repair 

doublers already installed in the 

affected areas that deviate from Boeing 

Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009; 

therefore, alternative inspection 

procedures are necessary for the 

repaired structure. JAL stated that it will 

have to obtain AMOC approval for each 

of its 14 airplanes. JAL also stated that 

since it takes additional work for both 

JAL and Boeing to obtain the AMOC 

approval, an exception should be 

allowed to admit all of the existing 

repairs as an AMOC for the proposed 

actions. JAL also proposed the 

alternative of an approval letter from the 

FAA for their existing repairs before the 

effective date of the AD. As an 

alternative, JAL requested a grace period 

to allow an extended compliance time 

for the inspection of previously repaired 

airplanes. 

We disagree with the request for 

AMOC approval for previously repaired 

airplanes and for a grace period. An 

AMOC cannot be included in an AD, 

because an AMOC can be written for an 

AD only after the AD is published. 

Because the repairs previously done on 

these 14 airplanes can be unique to each 

airplane and are different from the 

repair requirements of this AD, each 

instance will need to be re-evaluated for 

this AD as an AMOC to ensure 

continued operational safety. However, 

under the provisions of paragraph (u) of 

this AD, after the AD is published we 

will consider requests for approval of an 

alternative method of compliance if 

sufficient data are submitted to 

substantiate that the previous repairs 

would provide an acceptable level of 

safety. 

We also disagree with the request to 

include a grace period. A grace period 

of 1,500 flight hours from the effective 

date of this AD was already included in 

paragraphs (k), (o), and (r) of this AD. 

No change has been made to this AD. 

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 160 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

TABLE—ESTIMATED COSTS

Action Work hours Average labor rate 

per hour Cost per product Number of U.S.-registered airplanes Fleet cost 

Inspections: Body Skin and 

Skin Splice Plate.

1 $85 $85 160 .......................... $13,600. 

Modification: Groups 1–3 1 ....... 180 85 15,300 Up to 27 .................. Up to $413,100. 

Modification: Groups 1–3 2 ....... 320 85 27,200 Up to 27 .................. Up to $734,400. 

Modification: Groups 4–8 3 ....... 180 85 15,300 Up to 133 ................ Up to $2,034,900. 

Modification: Groups 4–7 4 ....... 40 85 3,400 Up to 44 .................. Up to $149,600. 

Post-Mod LFEC Inspection 5 .... 6 85 510 Up to 160 ................ Up to $81,600. 

Inspections: Bulkhead Outer 

Chord 6.

4 85 340 Up to 160 ................ Up to $54,400. 

1 Installation of skin and splice plate doubler for Groups 1–3 airplanes that have not done Boeing Service Bulletin 747–53–2150 or Figure 35 of 

Section 53–30–03 of the Boeing 747 Structural Repair Manual. 2 Installation of skin and splice plate doubler for Groups 1–3 airplanes that have done Boeing Service Bulletin 747–53–2150 or Figure 35 of 

Section 53–30–03 of the Boeing 747 Structural Repair Manual. 3 Installation of skin and splice plate doubler for Groups 4–8 airplanes. 

4 Installation of splice plate doubler for Groups 4–7 airplanes changed before Boeing Alert Service Bulletin 747–53A2305, Revision 2, dated 

January 15, 2009. 5 Inspection for skin cracks around the fasteners at the periphery of the modification doublers. 

6 Includes inspection of the frame web and body skin. 


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81432 Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 

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): 

2010–26–07 The Boeing Company: 

Amendment 39–16546; Docket No. 

FAA–2010–0674; Directorate Identifier 

2010–NM–012–AD. 

Effective Date 

(a) This AD is effective February 1, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to all The Boeing 

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

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

747–300, 747–400, 747–400D, 747–400F, 

747SR, and 747SP series airplanes, 

certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 53: Fuselage. 

Unsafe Condition 

(e) This AD results from reports of cracking 

of the fuselage skin and adjacent internal 

skin splice plate at the left and right nose 

wheel well aft corners, and the outer chord 

of the body station (BS) 400 bulkhead. The 

Federal Aviation Administration is issuing 

this AD to detect and correct cracking of the 

fuselage skin or splice plate, which, together 

with cracking of the bulkhead outer chord, 

could result in large skin cracks and 

subsequent in-flight rapid decompression 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. 

Pre-Modification Inspections 

(g) For airplanes in Groups 1 through 3, as 

identified in Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, that have not been modified in 

accordance with Boeing Service Bulletin 

747–53–2150; have not been repaired in 

accordance with Figure 35 of Section 53–30– 

03 of Boeing 747 Structural Repair Manual 

(SRM); and have not been modified in 

accordance with Boeing Alert Service 

Bulletin 747–53A2305: Before the 

accumulation of 3,000 total flight cycles, or 

within 1,500 flight cycles after the effective 

date of this AD, whichever occurs later, do 

an external detailed inspection for cracks in 

the body skin around the aft corners of the 

nose wheel well, and skin splice plate at the 

aft corners of the nose wheel well, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009. 

(h) For airplanes in Groups 1 through 3, as 

identified in Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, that have been modified in accordance 

with Boeing Service Bulletin 747–53–2150; 

or repaired in accordance with Figure 35 of 

Section 53–30–03 of Boeing 747 SRM: Within 

6,000 flight cycles after doing the 

modification or repair, or within 1,500 flight 

cycles after the effective date of this AD, 

whichever occurs later, do an external 

detailed inspection for cracks in the body 

skin around the aft corners of the nose wheel 

well, and skin splice plate at the aft corners 

of the nose wheel well, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009. 

(i) For airplanes in Groups 4 through 7, as 

identified in Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, that have not been modified in 

accordance with Boeing Alert Service 

Bulletin 747–53A2305: Prior to the 

accumulation of 3,000 total flight cycles, or 

within 1,500 flight cycles after the effective 

date of this AD, whichever occurs later, do 

an external detailed inspection for cracks in 

the body skin around the aft corners of the 

nose wheel well, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009. 

(j) For airplanes in Groups 4 through 7, as 

identified in Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, that have been modified in accordance 

with Boeing Service Bulletin 747–53–2305, 

dated June 27, 1991; or Revision 1, dated 

May 22, 1997: Within 1,000 flight cycles after 

the effective date of this AD, do a one-time 

external general visual inspection for steel 

cross-shaped doublers, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009. If no 

cross-shaped doublers are installed, within 

1,500 flight cycles after the effective date of 

this AD, install cross-shaped doublers, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009. 

(k) For airplanes in Group 8, as identified 

in Boeing Alert Service Bulletin 747– 

53A2305, Revision 2, dated January 15, 2009: 

Prior to the accumulation of 3,000 total flight 

cycles, or within 1,500 flight cycles after the 

effective date of this AD, whichever occurs 

later, do an external detailed inspection for 

cracks in the body skin around the aft corners 

of the nose wheel well, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009. 

(l) If no crack is found during any 

inspection required by paragraph (g), (h), (i), 

or (k) of this AD, repeat the applicable 

inspection specified in paragraph (g), (h), (i), 

or (k) of this AD thereafter at intervals not to 

exceed 1,500 flight cycles, until the 

modification specified in paragraph (n) of 

this AD is accomplished. 

(m) If any crack is found during any 

inspection required by paragraph (g), (h), (i), 

(k), or (l) of this AD, before further flight, 

modify the aft corners of the nose wheel well 

by installing modification doublers and 

doing all applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 


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Federal Register / Vol. 75, No. 248 / Tuesday, December 28, 2010 / Rules and Regulations 81433 

dated January 15, 2009, except as required by 

paragraph (t) of this AD. 

Optional Terminating Action 

(n) Modification of the aft corners of the 

nose wheel well by installing modification 

doublers and doing all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009, terminates the repetitive inspections 

required by paragraph (l) of this AD for the 

modified side only. Where Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009, specifies to contact 

Boeing for appropriate action, repair using a 

method approved in accordance with the 

procedures specified in paragraph (u) of this 

AD. 

Post-Modification Repetitive Inspections 

(o) For airplanes on which the 

modification specified in Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009, has been done: At the 

applicable time specified in paragraph (o)(1) 

or (o)(2) of this AD, do an external low 

frequency eddy current inspection for skin 

cracks around the fasteners at the periphery 

of the modification doublers, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009. 

(1) For airplanes on which the edge row 

fastener holes common to the external 

modification doublers have been zero-timed 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2305, Revision 2, dated January 15, 

2009: Within 15,000 flight cycles after 

accomplishing the modification, or within 

1,500 flight cycles after the effective date of 

this AD, whichever occurs later. 

(2) For airplanes on which the edge row 

fastener holes common to the external 

modification doublers have not been zerotimed in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009: Prior to the 

accumulation of 15,000 total flight cycles, or 

within 1,500 flight cycles after the effective 

date of this AD, whichever occurs later. 

(p) If no cracking is found during the 

inspection required by paragraph (o) of this 

AD, repeat the inspection specified in 

paragraph (o) of this AD thereafter at 

intervals not to exceed 1,500 flight cycles. 

(q) If any cracking is found during any 

inspection required by paragraph (o) or (p) of 

this AD, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (u) of this 

AD. 

Body Station (BS) 400 Bulkhead Outer 

Chord Inspection 

(r) For all airplanes: At the latest of the 

times specified in paragraphs (r)(1), (r)(2), 

and (r)(3) of this AD, do a surface HFEC 

inspection for cracking in the BS 400 

bulkhead outer chord, skin splice plate, and 

outer chord radius filler; and a detailed 

inspection for cracking of the bulkhead frame 

web and body skin; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2305, Revision 2, 

dated January 15, 2009. If no cracking is 

found during any inspection, repeat the 

inspection one time within 6,000 flight 

cycles, and thereafter at intervals not to 

exceed 3,000 flight cycles. 

(1) Before the accumulation of 20,000 total 

flight cycles. 

(2) Within 3,000 flight cycles after doing 

the HFEC inspection required by AD 2004– 

07–22 R1, Amendment 39–15326, for 

structural significant item (SSI) F–4B of the 

Boeing Document No. D6–35022, 

‘‘Supplemental Structural Inspection 

Document (SSID) for Model 747 Airplanes,’’ 

Revision G, dated December 2000. 

(3) Within 1,500 flight cycles after the 

effective date of this AD. 

(s) If any cracking is found during any 

inspection required by paragraph (r) of this 

AD, before further flight, repair in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009, except as 

required by paragraph (t) of this AD. Within 

6,000 flight cycles after doing the repair, do 

the inspections specified in paragraph (r) of 

this AD, and repeat the inspections thereafter 

at intervals not to exceed 3,000 flight cycles. 

Service Bulletin Exception 

(t) If any cracking is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2305, 

Revision 2, dated January 15, 2009, specifies 

to contact Boeing for appropriate action: 

Before further flight, repair the crack using a 

method approved in accordance with the 

procedures specified in paragraph (u) of this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(u)(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: Steven 

Fox, Senior Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6425; fax (425) 917–6590. 

Information may be e-mailed to: 9–ANM– 

Seattle-ACO–AMOC–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. 

Related Information 

(v) For more information about this AD, 

contact Steven Fox, Senior Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue, SW., Renton, Washington 

98057–3356; telephone (425) 917–6425; fax 

(425) 917–6590; e-mail: steven.fox@faa.gov. 

Material Incorporated by Reference 

(w) You must use Boeing Alert Service 

Bulletin 747–53A2305, Revision 2, dated 

January 15, 2009, to do the actions required 

by this AD, unless the AD specifies 

otherwise. The optional actions, if 

accomplished, shall be done in accordance 

with Boeing Alert Service Bulletin 747– 

53A2305, Revision 2, dated January 15, 2009. 

(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 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 

December 13, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–31985 Filed 12–27–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1201; Directorate 

Identifier 2010–NM–081–AD; Amendment 

39–16551; AD 2010–26–12] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A321–211, –212, –231, and –232 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 


srobinson on DSKHWCL6B1PROD with RULES