Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations 60889 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0491; Directorate 

Identifier 2011–NM–265–AD; Amendment 

39–17207; AD 2012–20–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–100, 

–200, and –200C series airplanes. This 

AD was prompted by a report of a 

severed upper butt strap, and cracks in 

the forward skin and bonded doubler, 

on one airplane. This AD requires 

repetitive inspections for cracks and a 

chemical spot test in the area of station 

(STA) 908, and related investigative and 

corrective actions, if necessary. For 

certain airplanes, this AD requires an 

inspection and modification. We are 

issuing this AD to prevent cracks at the 

adjacent mating skins (forward and aft), 

which could initiate just above stringers 

S–4R and S–4L; and could grow and 

result in a decompression event. 

DATES: This AD is effective November 9, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 9, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; 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, WA 98057–3356. 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: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6447; 

fax: (425) 917–6590; email: 

wayne.lockett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on June 4, 2012 (77 FR 32918). 

That NPRM proposed to require 

repetitive inspections for cracks and a 

chemical spot test in the area of STA 

908, and related investigative and 

corrective actions, if necessary. For 

certain airplanes, that NPRM also 

proposed to require an inspection and 

modification. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal (77 FR 32918, 

June 4, 2012) and the FAA’s response to 

the comment. 

Request To Relocate Terminating 

Action Statement 

Boeing requested that we relocate the 

terminating action statement related to 

confirmed 2000 series aluminum from 

paragraph (h)(2) of the NPRM (77 FR 

32918, June 4, 2012) to paragraph (j) of 

the NPRM. 

We disagree with the request to 

relocate the sentence. The terminating 

action specified in paragraph (h)(2) of 

this AD only terminates the actions 

specified in paragraph (h)(1) of this AD. 

Paragraph (j) of the AD allows operators 

to forego all requirements of this AD, 

including the initial inspection, 

repetitive inspections, and chemical 

spot test requirements, by replacing the 

butt strap with a new part made of the 

correct material, and doing related 

investigative and corrective actions, as 

applicable. No change has been made to 

the AD in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comment 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 61 

airplanes of U.S registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators 

Inspection and test ........ 166 work-hours × $85 per hour = $14,110 per 

inspection cycle.

$0 $14,110 per inspection 

cycle.

$860,710 per inspection 

cycle. 

In addition, we have received no 

definitive data that would enable us to 

provide cost estimates for the actions 

that would be required for Group 1 

airplanes. 

We estimate the following costs to do 

any necessary related investigative 

actions, repairs, and installations that 

would be required based on the results 

of the inspection and test. We have no 

way of determining the number of 

aircraft that might need these actions: 


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60890 Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Related investigative actions, repair, installation ......... 173 work-hours × $85 per hour = $14,705 .................. $0 $14,705 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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): 

2012–20–01 The Boeing Company: 

Amendment 39–17207; Docket No. 

FAA–2012–0491; Directorate Identifier 

2011–NM–265–AD. 

(a) Effective Date 

This AD is effective November 9, 2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–100, –200, and –200C series 

airplanes; certificated in any category; as 

identified in Boeing Special Attention 

Service Bulletin 737–53–1313, dated 

November 3, 2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53; Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

severed upper butt strap, and cracks in the 

forward skin and bonded doubler, on one 

airplane. We are issuing this AD to prevent 

cracks at the adjacent mating skins (forward 

and aft), which could initiate just above 

stringers S–4R and S–4L; and could grow and 

result in a decompression event. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Actions for Group 1 Airplanes 

For Group 1 airplanes, as identified in 

Boeing Special Attention Service Bulletin 

737–53–1313, dated November 3, 2011: 

Within 120 days after the effective date of 

this AD, inspect and modify, as required, 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(h) Actions for Groups 2 and 3 Airplanes 

For Groups 2 and 3 airplanes, as identified 

in Boeing Special Attention Service Bulletin 

737–53–1313, dated November 3, 2011: 

Except as provided by paragraph (i)(1) of this 

AD, at the applicable times identified in 

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

Special Attention Service Bulletin 737–53– 

1313, dated November 3, 2011, do the actions 

specified in paragraphs (h)(1) and (h)(2) of 

this AD, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1313, dated November 3, 2011, except as 

provided by paragraph (i)(2) of this AD. 

(1) Do one of the inspection options 

identified in paragraphs (h)(1)(i), (h)(1)(ii), 

and (h)(1)(iii) of this AD; and do all 

applicable related investigative and 

corrective actions. Do all applicable related 

investigative and corrective actions before 

further flight. 

(i) Inspection Option 1: Do a detailed 

inspection for cracks of the station (STA) 908 

forward and aft skin. Thereafter, repeat the 

inspection at intervals not to exceed 500 

flight cycles until the chemical spot test 

required by paragraph (h)(2) of this AD is 

done. 

(ii) Inspection Option 2: Do a one-time 

external low-frequency eddy current (LFEC) 

inspection for cracks of the STA 908 upper 

butt strap. 

(iii) Inspection Option 3: Do a one-time 

internal LFEC inspection for cracks of the 

STA 908 upper butt strap. 

(2) Do a chemical spot test of the STA 908 

upper butt strap to determine the part 

material, and do all applicable related 

investigative and corrective actions. Do all 

applicable related investigative and 

corrective actions at the times specified in 

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

Special Attention Service Bulletin 737–53– 

1313, dated November 3, 2011, except as 

provided by paragraph (i)(1) of this AD. 

Confirming the upper butt strap is made from 

2000 series aluminum terminates the 

inspections required by paragraph (h)(1) of 

this AD. 

(i) Exceptions to the Service Information 

(1) Where Boeing Special Attention Service 

Bulletin 737–53–1313, dated November 3, 

2011, specifies a compliance time ‘‘after the 

original issue date of the service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 737–53–1313, dated November 3, 

2011, specifies to contact Boeing for repair 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations 60891 

instructions: Before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (k) of 

this AD. 

(j) Terminating Action 

Replacing the STA 908 upper butt strap 

and doing all applicable related investigative 

and corrective actions, in accordance with 

Part 4, Part 5, and Part 6, of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1313, dated November 3, 2011, except as 

provided by paragraph (i)(2) of this AD, 

terminates the inspections and chemical spot 

test required by this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(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. 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 emailed 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. 

(l) Related Information 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6447; fax: (425) 917–6590; 

email: wayne.lockett@faa.gov. 

(m) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 737–53–1313, dated November 3, 

2011. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call (425) 227–1221. 

(5) You may view this 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/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

September 21, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–24280 Filed 10–4–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0492; Directorate 

Identifier 2010–NM–126–AD; Amendment 

39–17209; AD 2012–20–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 747 

airplanes. That AD currently requires 

repetitive visual inspections around the 

bushings of the wing landing gear 

(WLG) beam outboard end fittings for 

corrosion, and rework if necessary; and 

ultrasonic inspections for cracks of the 

outboard end fittings of the WLG 

support beams, and rework if necessary. 

This new AD adds airplanes and adds 

repetitive inspections of the outboard 

end fitting of the left and right WLG 

support beams for cracks and corrosion, 

and corrective actions if necessary. This 

AD was prompted by new reports of 

corrosion damage to the end fittings of 

the WLG support beams, and one report 

of subsequent cracking in the end 

fittings. We are issuing this AD to detect 

and correct corrosion and subsequent 

cracking in the outboard end fittings, 

which could result in separation of the 

fitting and damage to adjacent flight 

control cables and hydraulic systems 

and consequent reduced controllability 

of the airplane. 

DATES: This AD is effective November 9, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 9, 2012. 

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; 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6432; 

fax: (425) 917–6590; email: 

bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 89–15–07, 

Amendment 39–6267 (54 FR 30009, July 

18, 1989). That AD applies to the 

specified products. The NPRM 

published in the Federal Register on 

May 31, 2012 (77 FR 32064). That 

NPRM proposed to continue to require 

repetitive visual inspections around the 

bushings of the wing landing gear 

(WLG) beam outboard end fittings for 

corrosion, and rework if necessary; and 

ultrasonic inspections for cracks of the 

outboard end fittings of the WLG 

support beams, and rework if necessary. 

That NPRM also proposed to add 

airplanes and repetitive inspections of 

the outboard end fitting of the left and 

right WLG support beams for cracks and 


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