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 


pmangrum on DSK3VPTVN1PROD with RULES
60892 Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations 

corrosion, and corrective actions if 

necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 32064, 

May 31, 2012) and the FAA’s response 

to each comment. 

Request To Change Certain Language in 

Paragraph (s) of the NPRM (77 FR 

32064, May 31, 2012) 

Boeing asked that the following 

sentence be added to paragraph (s) of 

the NPRM (77 FR 32064, May 31, 2012): 

‘‘After accomplishing the repair or 

change in accordance with Part 7 of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2331, 

dated November 12, 2009, do the 

applicable actions required by 

paragraph (r) of this AD.’’ Boeing stated 

that the follow-on inspections are 

required after accomplishing the repair 

or replacement in Part 7. Boeing added 

that paragraph (q) of the NPRM contains 

a similar requirement for Groups 1 

through 5 airplanes. 

We partially agree with the 

commenter. We agree that the language 

specified in paragraphs (q) and (s) of the 

NPRM (77 FR 32064, May 31, 2012) is 

inconsistent. However, we do not agree 

to include the additional sentence in 

paragraph (s) of this final rule because 

it would continue to restate redundant 

information, and may further confuse 

operators. Therefore, we have removed 

‘‘* * * do the applicable actions 

required by paragraph (p) of this AD,’’ 

as was specified in paragraph (q) of the 

NPRM, in order to provide consistency 

between those related paragraphs. 

Request To Include Certain Part 

Numbers (P/Ns) in the NPRM (77 FR 

32064, May 31, 2012) 

Qantas Airways (QAN) asked that the 

NPRM (77 FR 32064, May 31, 2012) be 

reviewed to accurately capture all 

approved part numbers for end fitting 

replacements. QAN stated that, for its 

Model 747–400 Configuration 6 

airplanes, Boeing Alert Service Bulletin 

747–57A2331, dated November 12, 

2009, specifies that if a replacement 

spare end fitting is required, an end 

fitting assembly having P/N 112U1701– 

1 is to be used for that replacement. 

QAN noted that the parts page inventory 

list from the original equipment 

manufacturer (OEM) shows that P/N 

112U1701–1 is no longer available and 

has been replaced with P/N 112U2701– 

7. QAN also noted that P/N 65B14473– 

23 and P/N 65B14473–24 are no longer 

available and have been replaced by P/ 

N 65B14473–33 and P/N 65B14473–34, 

respectively. QAN added that these 

replacement parts are not identified in 

the referenced service information. QAN 

also stated that, if any of the 

replacement parts are used, it will be 

forced to request an alternative method 

of compliance (AMOC) from the OEM to 

approve the use of an alternate part in 

order to comply with the AD 

requirements. 

We acknowledge the commenter’s 

concerns. However, as specified in the 

NPRM (77 FR 32064, May 31, 2012), 

since issuance of AD 89–15–07, 

Amendment 39–6267 (54 FR 30009, July 

18, 1989), corrosion occurred again at 

the lug bore and bushing interface 

because moisture continued to develop 

in that area due to exposure of the end 

fittings to environmental conditions. 

Subsequently, cracks occurred at the 

corroded areas of the end fittings; 

therefore, the unsafe condition specified 

in the existing AD has not been 

corrected. We find that issuing this AD 

without further delay is necessary to 

adequately address the identified unsafe 

condition. Operators may submit a 

request for approval of the replacement 

part numbers (P/Ns) through an AMOC, 

as specified in paragraph (u) of the AD. 

We have not changed the AD in this 

regard. 

Request To Change Certain Paragraph 

Identifiers in the NPRM (77 FR 32064, 

May 31, 2012) 

Boeing and Atlas Air asked that the 

paragraph identifier in the last sentence 

in paragraph (l) of the NPRM (77 FR 

32064, May 31, 2012) be changed from 

paragraph (j) to paragraph (p). Boeing 

and Atlas Air stated that paragraph (j) of 

the NPRM would not be applicable 

since it applies to inspections of the end 

fittings prior to accomplishing the repair 

or replacement in Part 7 of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. Atlas Air added 

that paragraph (p) of the NPRM defines 

the procedures for follow-on end fitting 

inspections on which the repair or 

replacement specified in Part 7 has been 

done. 

Boeing, Atlas Air, and UPS asked that 

the paragraph identifier in the last 

sentence in paragraph (n) of the NPRM 

(77 FR 32064, May 31, 2012) be changed 

from paragraph (m) to paragraph (r). 

Boeing, Atlas Air, and UPS stated that 

paragraph (m) of the NPRM applies to 

inspections of the end fittings prior to 

accomplishing the repair or replacement 

in Part 7 of Boeing Alert Service 

Bulletin 747–57A2331, dated November 

12, 2009. Atlas Air added that paragraph 

(r) of the NPRM defines the procedures 

for follow-on end fitting inspections on 

which the repair or replacement 

specified in Part 7 has been done. 

We agree with the commenters for the 

reasons provided. We have changed the 

paragraph identifiers in paragraphs (l) 

and (n) of this AD accordingly. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We also determined that these changes 

will not increase the economic burden 

on any operator or increase the scope of 

the AD. 

Explanation of Change to Costs of 

Compliance 

Since issuance of AD 89–15–07, 

Amendment 39–6267 (54 FR 30009, July 

18, 1989), we have increased the labor 

rate used in the Costs of Compliance 

from $40 per work-hour to $85 per 

work-hour. The Costs of Compliance 

information, below, reflects this 

increase in the specified labor rate. 

Costs of Compliance 

We estimate that this AD affects 173 

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 

Inspections [retained actions 

from existing AD 89–15–07, 

Amendment 39-6267 (54 

FR 30009, July 18, 1989)].

10 work-hours × $85 per hour 

= $850 per inspection cycle.

$0 $850 per inspection cycle ...... $147,050 per inspection 

cycle. 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations 60893 

ESTIMATED COSTS—Continued 

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

Inspections [new action] ......... Up to 67 work-hours × $85 

per hour = $5,695 per inspection cycle, depending 

on configuration.

$0 Up to $5,695 per inspection 

cycle, depending on configuration.

Up to $985,235 per inspection 

cycle, depending on configuration. 

We estimate the following costs to do 

any necessary repairs/replacements that 

would be required based on the results 

of the inspection. We have no way of 

determining the number of aircraft that 

might need these repairs/replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair or replacement ................... Up to 71 work-hours × $85 per 

hour = $6,035, depending on 

configuration.

Up to $26,436, depending on configuration.Up to $32,471, depending on 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), 

(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 

removing airworthiness directive (AD) 

89–15–07, Amendment 39–6267 (54 FR 

30009, July 18, 1989), and adding the 

following new AD: 

2012–20–03 The Boeing Company: 

Amendment 39–17209; Docket No. 

FAA–2012–0492; Directorate Identifier 

2010–NM–126–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective November 9, 2012. 

(b) Affected ADs 

This AD supersedes AD 89–15–07, 

Amendment 39–6267 (54 FR 30009, July 18, 

1989). 

(c) Applicability 

This AD applies to 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; as identified in Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by new reports of 

corrosion damage to the end fittings of the 

wing landing gear (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. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Repetitive Inspections With 

Revised Compliance Times 

This paragraph restates the requirements of 

paragraphs A., B., C., and D., of AD 89–15– 

07, Amendment 39–6267 (54 FR 30009, July 

18, 1989) with revised compliance times. For 

airplanes identified in Boeing Service 

Bulletin 747–57–2244, Revision 1, dated July 

28, 1988: Prior to the accumulation of 30,000 

flight hours or 8 years in service, whichever 

occurs first; or within the next 14 months 

after August 22, 1989 (the effective date of 

AD 89–15–07); whichever occurs later; 

visually inspect around the fitting lug 

bushings at the WLG beam outboard end 

fittings for corrosion, and ultrasonically 

inspect the WLG beam outboard end fittings 

for cracks, in accordance with Boeing Service 

Bulletin 747–57–2244, Revision 1, dated July 

28, 1988. Accomplishing the initial 

inspections required by paragraph (j) of this 

AD terminates the inspections required by 

this paragraph. 

(1) If no cracking or corrosion is found, 

repeat the inspections at intervals not to 

exceed 18 months until paragraph (j) of this 

AD has been accomplished. 

(2) If cracking is found, prior to further 

flight, remove the WLG beam outboard 


pmangrum on DSK3VPTVN1PROD with RULES
60894 Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations 

fitting, and rework, in accordance with 

Boeing Service Bulletin 747–57–2244, 

Revision 1, dated July 28, 1988. 

(3) If only corrosion is found, within the 

next 12 months, rework in accordance with 

Boeing Service Bulletin 747–57–2244, 

Revision 1, dated July 28, 1988. The 

ultrasonic inspections for cracks required by 

paragraph (g) of this AD must be 

accomplished at intervals not to exceed 6 

months until the rework is accomplished. For 

any corrosion that is found after the effective 

date of this AD, the rework must be done 

before further flight. 

(h) Retained Terminating Action 

This paragraph restates the requirements of 

paragraph E., of AD 89–15–07, Amendment 

39–6267 (54 FR 30009, July 18, 1989). 

Terminating action for the inspections 

required by paragraph (g) of this AD consists 

of rework of the WLG beam outboard fittings, 

in accordance with Boeing Service Bulletin 

747–57–2244, Revision 1, dated July 28, 

1988. 

(i) New Compliance Times for This AD 

For all the actions identified in paragraphs 

(j) through (t) of this AD, do the actions at 

the applicable time specified in paragraph 

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

Bulletin 747–57A2331, dated November 12, 

2009. Where paragraph 1.E., ‘‘Compliance’’ of 

this service bulletin specifies a compliance 

time relative to the original issue date of the 

service bulletin, this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(j) New Repetitive Inspections for Groups 1 

Through 5 Airplanes 

For Groups 1 through 3 airplanes, 

Configurations 1 and 2; and Groups 4 and 5 

airplanes: Do detailed and ultrasonic 

inspections of the end fittings for cracks and 

corrosion, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(k) New Inspections for No Crack or 

Corrosion Findings for Groups 1 Through 5 

Airplanes 

If no crack or corrosion is found during any 

inspection required by paragraph (j) of this 

AD, do either of the actions required by 

paragraph (k)(1) or (k)(2) of this AD. 

(1) Repeat the detailed and ultrasonic 

inspections of the end fittings for cracks and 

corrosion, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(2) Do a detailed inspection of the end 

fittings for fillet seal damage and for cracks 

and corrosion, in accordance with Part 2 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(i) If no fillet seal damage, crack, or 

corrosion is found: Repeat the inspection 

required by paragraph (k)(2) of this AD. 

(ii) If any fillet seal damage is found, but 

no crack or corrosion is found: Remove the 

fillet seal, and do detailed and HFEC 

inspections of each end fitting for cracks and 

corrosion, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (l) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(1) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, and thereafter repeat the 

inspections required by paragraph 

(k)(2)(ii)(B) of this AD. 

(2) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (l) of this AD. 

(l) New Repair for Crack or Corrosion 

Findings for Groups 1 Through 5 Airplanes 

If any crack or corrosion is found during 

any inspection required by paragraph (j) or 

(k) of this AD: Repair or change the end 

fitting, in accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. After accomplishing the 

repair or change in accordance with Part 7 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2331, dated 

November 12, 2009, do the applicable actions 

required by paragraph (p) of this AD. 

(m) New Repetitive Inspections and 

Corrective Actions for Group 6 Airplanes 

For Group 6 airplanes: Do a detailed 

inspection of the end fittings for fillet seal 

damage and for cracks and corrosion, in 

accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(1) If no fillet seal damage, crack, or 

corrosion is found: Do the detailed 

inspection of the end fittings for fillet seal 

damage and for cracks and corrosion, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(i) If no fillet seal damage, crack, or 

corrosion is found: Repeat the detailed 

inspection required by paragraph (m)(1) of 

this AD. 

(ii) If any fillet seal damage is found, but 

no crack or corrosion is found: Remove the 

fillet seal, and do detailed and HFEC 

inspections of each end fitting for cracks and 

corrosion, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (n) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(1) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (n) of this AD. 

(2) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, and thereafter repeat the 

inspections required by paragraph 

(m)(1)(ii)(B) of this AD. 

(2) If any fillet seal damage is found, but 

no crack or corrosion is found: Remove the 

fillet seal, and do detailed and HFEC 

inspections of each end fitting for cracks and 

corrosion, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(i) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (n) of this AD. 

(ii) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with paragraph (n) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, and thereafter repeat the 

inspections required by paragraph (m)(2)(ii) 

of this AD. 

(n) New Repair for Group 6 Airplanes 

If any crack or corrosion is found during 

any inspection required by paragraph (m) of 

this AD: Repair or change the end fitting, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. After accomplishing the 

repair or change in accordance with Part 7 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–57A2331, dated 

November 12, 2009, do the applicable actions 

required by paragraph (r) of this AD. 

(o) New Optional Terminating Action for 

Part 1, Part 2, and Part 3 Inspections 

In lieu of doing Part 1, Part 2, or Part 3 

inspections required by this AD: Repair or 

change the end fitting, in accordance with 

Part 7 of the Accomplishment Instructions of 


pmangrum on DSK3VPTVN1PROD with RULES
Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations 60895 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. After 

accomplishing the repair or change in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, do the applicable actions 

required by paragraphs (p) and (r) of this AD. 

Doing the repair or change terminates the 

Part 1, 2, or 3 inspections for that part only 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(p) New Follow-On End Fitting Inspection 

for Groups 1 Through 5 Airplanes 

For Groups 1 through 5 airplanes on which 

the repair or change specified in Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, has been done: Do 

detailed and ultrasonic inspections of the 

end fittings for cracks and corrosion, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. If no crack or corrosion 

is found, do the actions required by either 

paragraph (p)(1) or (p)(2) of this AD. 

(1) Repeat the detailed and ultrasonic 

inspections of the end fittings for cracks and 

corrosion required by paragraph (p) of this 

AD. 

(2) Do a detailed inspection of each end 

fitting for fillet seal damage, cracks, and 

corrosion, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(i) If no fillet seal damage, crack, or 

corrosion is found: Repeat the inspection 

required by paragraph (p)(2) of this AD. 

(ii) If any fillet seal damage is found, but 

no crack or corrosion is found: Remove the 

fillet seal, and do detailed and HFEC 

inspections of each end fitting for cracks and 

corrosion, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, as required 

by paragraph (q) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(1) If any crack or corrosion is found: 

Repair or change the end fitting, as required 

by paragraph (q) of this AD. 

(2) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and repeat the detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(q) New Repair for Groups 1 Through 5 

Airplanes 

If any crack or corrosion is found during 

any inspection required by paragraph (p) of 

this AD, repair or change the end fitting, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(r) New Follow-On End Fitting Inspection for 

Group 6 Airplanes 

For Group 6 airplanes on which the repair 

or change specified in Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, has been done: Do a 

detailed inspection of the end fittings for 

fillet seal damage, cracks, and corrosion, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(1) If no fillet seal damage, crack, or 

corrosion is found: Do a detailed inspection 

of each end fitting for fillet seal damage, 

cracks, and corrosion, in accordance with 

Part 5 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(i) If no fillet seal damage, crack, or 

corrosion is found: Repeat the inspection 

required by paragraph (r)(1) of this AD. 

(ii) If any fillet seal damage is found, but 

no crack or corrosion is found: Do detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

5 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting as required 

by paragraph (s) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and repeat the detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(1) If any crack or corrosion is found: 

Repair or change the end fitting, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(2) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and repeat the detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(2) If any fillet seal damage is found, but 

no crack or corrosion is found: Do detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

4 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(i) If any crack or corrosion is found: 

Repair or change the end fitting, as required 

by paragraph (s) of this AD. 

(ii) If no crack or corrosion is found: Apply 

corrosion inhibiting compound on each end 

fitting, in accordance with Part 4 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and do detailed and 

HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(A) If any crack or corrosion is found: 

Repair or change the end fitting, as required 

by paragraph (s) of this AD. 

(B) If no crack or corrosion is found: Apply 

corrosion inhibiting compound, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009; and repeat the detailed 

and HFEC inspections of each end fitting for 

cracks and corrosion, in accordance with Part 

6 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. 

(s) New Repair for Group 6 Airplanes 

If any crack or corrosion is found during 

any inspection required by paragraph (r) of 

this AD, repair or change the end fitting, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009. 

(t) New Optional Action for Part 4, Part 5, 

and Part 6 Inspections 

In lieu of doing Part 4, Part 5, or Part 6 

inspections required by this AD: Repair or 

change the end fitting, in accordance with 

Part 7 of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–57A2331, 

dated November 12, 2009. After 

accomplishing the repair or change in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–57A2331, dated 

November 12, 2009, do the applicable actions 

required by paragraphs (p) and (r) of this AD. 

(u) 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 


pmangrum on DSK3VPTVN1PROD with RULES
60896 Federal Register / Vol. 77, No. 194 / Friday, October 5, 2012 / Rules and Regulations 

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. 

(4) AMOCs approved previously in 

accordance with AD 89–15–07, Amendment 

39–6267 (54 FR 30009, July 18, 1989), are 

approved as AMOCs for the corresponding 

requirements of this AD. 

(v) Related Information 

(1) For more information about this AD, 

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. 

(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; 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. 

(w) 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 Alert Service Bulletin 747– 

57A2331, dated November 12, 2009. 

(ii) Boeing Service Bulletin 747–57–2244, 

Revision 1, dated July 28, 1988. 

(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; 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 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 26, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–24412 Filed 10–4–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Part 117 

[Docket No. USCG–2012–0888] 

Drawbridge Operation Regulation; 

Delaware River, Between Burlington, 

NJ and Bristol, PA 

AGENCY: Coast Guard, DHS. 

ACTION: Notice of temporary deviation 

from regulations. 

SUMMARY: The Commander, Fifth Coast 

Guard District, has issued a temporary 

deviation from the regulations 

governing the operation of the 

Burlington-Bristol Bridge on Route 413, 

across the Delaware River, at mile 117.8, 

between Burlington, NJ and Bristol, PA. 

This deviation restricts the operation of 

the draw span in order to facilitate the 

adjustment of the operating lift cables. 

DATES: This deviation is effective from 

7 a.m. on October 30, 2012 to 3 p.m. on 

November 1, 2012. 

ADDRESSES: Documents mentioned in 

this preamble as being available in the 

docket are part of docket USCG–2012– 

0888 and are available online by going 

to http://www.regulations.gov, inserting 

USCG–2012–0888 in the ‘‘Keyword’’ 

box and then clicking ‘‘Search’’. They 

are also available for inspection or 

copying at the Docket Management 

Facility (M–30), U.S. Department of 

Transportation, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

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

through Friday, except Federal holidays. 

FOR FURTHER INFORMATION CONTACT: If 

you have questions on this rule, call or 

email Terrance Knowles, Environmental 

Protection Specialist, Fifth Coast Guard 

District; telephone 757–398–6587, email 

Terrance.A.Knowles@uscg.mil. If you 

have questions on viewing the docket, 

call Renee V. Wright, Program Manager, 

Docket Operations, telephone 202–366– 

9826. 

SUPPLEMENTARY INFORMATION: The 

Burlington County Bridge Commission, 

who owns and operates this vertical-lift 

type drawbridge, has requested a 

temporary deviation from the current 

operating regulations set out in 33 CFR 

117.5 and 117.716(b) to facilitate the 

adjustment of the operational lift cables. 

The Burlington-Bristol Bridge on 

Route 413, at mile 117.8, across the 

Delaware River, between Burlington NJ 

and Bristol PA, has a vertical clearance 

in the closed position to vessels of 62 

feet above mean high water. 

Under the regular operating schedule 

the bridge opens on signal as required 

by 33 CFR 117.5 and the opening of a 

bridge may not be delayed more than 

five minutes for a highway bridge, after 

the signal to open is given as required 

by 33 CFR 117.716(b). 

Under this temporary deviation, the 

Burlington-Bristol Bridge will be closed 

to navigation and unable to open on 

signal each day from 7 a.m. until 3 p.m. 

on October 30, 2012 and November 1, 

2012. 

Vessels that can pass under the bridge 

without a drawbridge opening may do 

so at all times. There are no alternate 

routes for vessels transiting this section 

of the Delaware River. 

There are approximately four to six 

vessels per week from four facilities 

whose vertical clearance surpasses the 

closed bridge position, requiring an 

opening of the draw span. The Coast 

Guard has coordinated this replacement 

work with the Mariners’ Advisory 

Committee for the Bay & River 

Delaware, and will inform the other 

users of the waterway through our Local 

and Broadcast Notices to Mariners of the 

closure periods for the bridge so that 

vessels can arrange their transits to 

minimize any impact caused by the 

temporary deviation. The bridge will 

not be able to open in an emergency 

during lift cable tension adjustments. 

In accordance with 33 CFR 117.35(e), 

the drawbridge must return to its regular 

operating schedule immediately at the 

end of the designated time period. This 

deviation from the operating regulations 

is authorized under 33 CFR 117.35. 

Dated: September 25, 2012. 

Waverly W. Gregory, Jr., 

Bridge Program Manager, Fifth Coast Guard 

District. 

[FR Doc. 2012–24598 Filed 10–4–12; 8:45 am] 

BILLING CODE 9110–04–P 


pmangrum on DSK3VPTVN1PROD with RULES