Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 75827 

Internet https://techpubs.services/messierdowty.com. 

(4) You may review copies of the service 

information at the 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 

December 5, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30370 Filed 12–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1228; Directorate 

Identifier 2012–NM–190–AD; Amendment 

39–17292; AD 2012–25–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

certain The Boeing Company Model 

757–200, -200CB, and -300 series 

airplanes. That AD currently requires 

initial and repetitive inspections of the 

fuselage skin and bear strap at the 

forward, upper corner of the L1 entry 

door cutout for cracking, and repair if 

necessary. That action also provides an 

optional terminating action for the 

repetitive inspections. That AD also 

requires additional inspections for 

airplanes having repairs or preventative 

modifications installed and inspections 

for certain other airplanes. This AD 

requires the previous actions with 

additional airplane group configurations 

added to paragraph (n) of this AD. This 

AD was prompted by a determination 

that certain airplane group 

configurations in paragraph (n) of the 

existing AD were inadvertently removed 

in the final rule. We are issuing this AD 

to detect and correct cracking of the 

fuselage skin and bear strap at the 

forward upper corner of the L1 entry 

door cutout, which could result in 

reduced structural integrity of the L1 

entry door, and consequent rapid 

decompression of the airplane. 

DATES: This AD is effective January 10, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 3, 2012 (77 FR 52212, 

August 29, 2012). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 24, 2004 (69 FR 

25481, May 7, 2004). 

We must receive any comments on 

this AD by February 11, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, 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 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. 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 street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6440; fax: 

425–917–6590; email: 

nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 23, 2012, we issued AD 2012– 

15–15, Amendment 39–17144 (77 FR 

52212, August 29, 2012), which 

superseded AD 2004–09–32, 

Amendment 39–13622 (69 FR 25481, 

May 7, 2004), for certain The Boeing 

Company Model 757–200, -200CB, and 

-300 series airplanes. AD 2012–15–15 

requires initial and repetitive 

inspections of the fuselage skin and bear 

strap at the forward, upper corner of the 

L1 entry door cutout for cracking, and 

repair if necessary. That action also 

provides an optional terminating action 

for the repetitive inspections. That AD 

also requires additional inspections for 

airplanes having repairs or preventative 

modifications installed and inspections 

for certain other airplanes. That AD 

resulted from reports of additional 

cracking in the fuselage skin. We issued 

that AD to detect and correct cracking 

of the fuselage skin and bear strap at the 

forward upper corner of the L1 entry 

door cutout, which could result in 

reduced structural integrity of the L1 

entry door, and consequent rapid 

decompression of the airplane. 

Actions Since AD Was Issued 

Since we issued AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, 

August 29, 2012), it was noted that 

certain airplane group configurations 

included in paragraph (n) of the NPRM 

were inadvertently removed in the final 

rule. This AD includes Group 1, 

Configuration 4, and Group 2, 

Configuration 3, in paragraph (n) of this 

AD. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires retaining all 

requirements of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, 

August 29, 2012). 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 


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75828 Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 

rule because all actions of AD 2012–15– 

15, Amendment 39–17144 (77 FR 

52212, August 29, 2012), are retained 

and include certain airplane group 

configurations in paragraph (n) of this 

AD that were specified in the NPRM (76 

FR 81890, December 29, 2011), but were 

inadvertently removed in the final rule 

of AD 2012–15–15. Therefore, we find 

that notice and opportunity for prior 

public comment are unnecessary and 

that good cause exists for making this 

amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments before it becomes effective. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2012–1228 and directorate 

identifier 2012–NM–190–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 591 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Workhours 

Average 

labor rate 

per hour 

Cost per airplane 

Number of 

U.S.- 

registered 

airplanes 

Fleet cost 

Inspections (retained actions from existing AD 2012-15-15, Amendment 

39-17144 (77 FR 52212, August 29, 

2012)).

2 $85 $170 per inspection cycle ..... 57 $9,690 per inspection cycle. 

Inspection (retained actions from existing AD 2012–15–15, Amendment 

39-17144 (77 FR 52212, August 29, 

2012)).

3 $85 $255 per inspection cycle ..... 591 $150,705 per inspection cycle. 

Supplemental inspection (retained actions from existing AD 2012–15–15, 

Amendment 39-17144 (77 FR 

52212, August 29, 2012)).

15 $85 $1,275 per inspection cycle .. 591 $753,525 per inspection cycle. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspections. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair (retained actions from existing AD 

2012-15–15, Amendment 39-17144 (77 FR 

52212, August 29, 2012)).

Up to 26 work-hours × $85 = 

Up to $2,210.

Up to $2,661 Up to $4,871 depending on configuration. 

Preventive modification (retained actions from 

existing AD 2012–15–15, Amendment 

39-17144 (77 FR 52212, August 29, 2012)).

18 work-hours × $85 = $1,530 $1,338 .......... $2,868 

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. 


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Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 75829 

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 part 39 of the Federal 

Aviation Regulations (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) 

2012–15–15, Amendment 39–17144 (77 

FR 52212, August 29, 2012), and adding 

the following new AD: 

2012–25–11 The Boeing Company: 

Amendment 39–17292; Docket No. 

FAA–2012–1228; Directorate Identifier 

2012–NM–190–AD. 

(a) Effective Date 

This AD is effective January 10, 2013. 

(b) Affected ADs 

This AD supersedes AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 757–200, -200CB, and -300 

series airplanes, certificated in any category. 

Model 757–200PF series airplanes are not 

affected by this AD. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53: Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in the fuselage skin and bear strap at the 

forward upper corner of the L1 entry door 

cutout. We are issuing this AD to detect and 

correct cracking of the fuselage skin and bear 

strap at the forward, upper corner of the L1 

entry door cutout, which could result in 

reduced structural integrity of the L1 entry 

door and consequent rapid decompression of 

the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Initial Inspection With 

Terminating Action 

This paragraph restates the requirements of 

paragraph (g) of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012), with a terminating action. For 

airplanes having line numbers 1 through 90 

inclusive: Within 500 flight cycles after May 

24, 2004 (the effective date of AD 2004–09– 

32, Amendment 39–13622 (69 FR 25481, May 

7, 2004)), or within 90 days after May 24, 

2004 (the effective date of AD 2004–09–32), 

whichever occurs later, do the inspections of 

the forward upper corner of the L1 entry door 

cutout specified in paragraphs (g)(1), (g)(2), 

and (g)(3) of this AD, per Part 1 of the Work 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0089, dated March 

18, 2004, until the initial inspection required 

by paragraph (k) of this AD has been done. 

Doing the repair specified in paragraph (i) or 

(l) of this AD, or doing the preventive 

modification specified in paragraph (j) of this 

AD, terminates the inspections required by 

this paragraph. 

(1) Do a high frequency eddy current 

(HFEC) inspection for cracking of the 

fuselage skin around the adjacent fasteners. 

(2) Do an HFEC inspection for cracking 

along the edge of the skin and bear strap. 

(3) Do a low frequency eddy current (LFEC) 

inspection for cracking of the bear strap 

around each fastener. 

(h) Retained Repetitive Inspections and 

Terminating Modification When No Crack Is 

Detected 

This paragraph restates the requirements of 

paragraph (h) of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012), with a terminating modification. If 

no crack is detected during any inspection 

required by paragraph (g) of this AD: Repeat 

the inspections required by paragraph (g) of 

this AD at intervals not to exceed 1,400 flight 

cycles, until the requirements of paragraph 

(k) of this AD are done. Doing the repair 

specified in paragraph (i) or (l) of this AD, 

or doing the preventive modification 

specified in paragraph (j) of this AD, as 

applicable, terminates the repetitive 

inspections required by this paragraph. 

(i) Retained Repair, With Repair Option 

When Any Crack Is Detected 

This paragraph restates the requirements of 

paragraph (i) of AD 2012–15–15, Amendment 

39–17144 (77 FR 52212, August 29, 2012), 

with a repair option. If any crack is detected 

during any inspection required by paragraph 

(g) or (h) of this AD, and Boeing Special 

Attention Service Bulletin 757–53–0089, 

dated March 18, 2004, specifies to contact 

Boeing for appropriate action: Before further 

flight, repair, in accordance with a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), FAA; or in 

accordance with data meeting the type 

certification basis of the airplane approved 

by the Boeing Commercial Airplanes 

Organization Designation Authorization 

(ODA) that has been authorized by the 

Manager, Seattle ACO, to make such 

findings; or using a method approved in 

accordance with the procedures specified in 

paragraph (r) of this AD. For a repair method 

to be approved, the approval must 

specifically reference this AD. Doing the 

repair terminates the inspections required by 

paragraphs (g) and (h) of this AD. 

(j) Retained Optional Preventive 

Modification 

This paragraph restates the optional 

preventive modification specified in 

paragraph (j) of AD 2012–15–15, Amendment 

39–17144 (77 FR 52212, August 29, 2012). As 

an alternative to accomplishing the 

inspections required by paragraphs (g) and 

(h) of this AD, do the optional preventative 

modification of the forward upper corner of 

the L1 entry door cutout, and do all 

applicable related investigative/corrective 

actions, by accomplishing all the actions 

specified in Part 2 of the Work Instructions 

of Boeing Special Attention Service Bulletin 

757–53–0089, dated March 18, 2004. 

Accomplishment of the modification 

constitutes terminating action for the 

inspections required by paragraphs (g) and 

(h) of this AD. 

(k) Retained Inspections 

This paragraph restates the requirements of 

paragraph (k) of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012). For airplanes in Group 1, 

Configurations 1 and 2, and Group 2, 

Configuration 1, as defined in Boeing Special 

Attention Service Bulletin 757–53–0094, 

Revision 1, dated August 12, 2009: Except as 

provided by paragraph (p)(1) of this AD, at 

the applicable times specified in paragraph 

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

Attention Service Bulletin 757–53–0094, 

Revision 1, dated August 12, 2009, do HFEC 

and LFEC inspections for cracking of the skin 

and bear strap at the forward upper corner of 

the L1 entry door cutout, in accordance with 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–53– 

0094, Revision 1, dated August 12, 2009, 

except as provided by paragraph (p) of this 

AD. Repeat the inspections thereafter at 

intervals not to exceed 1,400 flight cycles. 

Doing the initial inspection required by this 

paragraph terminates the inspections 

required by paragraphs (g) and (h) of this AD. 

Doing the repair specified in paragraph (l) of 

this AD, or doing the optional preventive 

modification specified in paragraph (m) of 

this AD, terminates the inspections required 

by this paragraph. 

(l) Retained Terminating Repair 

This paragraph restates the terminating 

repair specified in paragraph (l) of AD 2012– 

15–15, Amendment 39–17144 (77 FR 52212, 

August 29, 2012). If any cracking is found 

during any inspection required by paragraph 

(k) of this AD, before further flight, repair in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0094, Revision 1, 

dated August 12, 2009, except as required by 

paragraph (p) of this AD. Doing the repair 

terminates the repetitive inspections required 

by paragraph (k) of this AD. 

(m) Retained Optional Preventive 

Modification 

This paragraph restates the optional 

preventive modification specified in 

paragraph (m) of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012). Accomplishing the optional 

preventive modification, in accordance with 


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the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–53– 

0094, Revision 1, dated August 12, 2009, 

except as provided by paragraph (p) of this 

AD, terminates the repetitive inspections 

required by paragraph (k) of this AD. 

(n) Retained Inspections and Repair With 

New Airplane Group Configurations 

This paragraph restates the requirements of 

paragraph (n) of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012), with new airplane group 

configurations. For airplanes in Group 1, 

Configurations 3, 4, and 5; and Group 2, 

Configurations 2, 3, and 4; as identified in 

Boeing Special Attention Service Bulletin 

757–53–0094, Revision 1, dated August 12, 

2009; with a repair doubler; a doubler and a 

tripler; or a doubler, tripler, and quadrupler 

installed; or with a preventive modification 

doubler installed: At the applicable times 

specified in paragraph 1.E, ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0094, Revision 1, dated August 12, 

2009, except as required by paragraph (p)(2) 

of this AD, do LFEC, HFEC, and detailed 

inspections, as applicable, for cracking of the 

doubler, tripler, quadrupler, skin, bear strap, 

and inner chord strap, as applicable, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0094, Revision 1, 

dated August 12, 2009. Repeat the 

inspections thereafter at the applicable times 

specified in paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Special Attention Service Bulletin 

757–53–0094, Revision 1, dated August 12, 

2009. 

(o) Retained Repair 

This paragraph restates the requirements of 

paragraph (o) of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012). If any cracking is found during any 

inspection required by paragraph (n) of this 

AD, before further flight, repair the crack in 

accordance with the procedures specified in 

paragraph (r) of this AD. 

(p) Retained Exceptions to Service Bulletin 

Specifications 

This paragraph restates the exceptions 

specified in paragraph (p) of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012). The following exceptions apply to 

this AD. 

(1) Where Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009, specifies a compliance time 

after the ‘‘original issue date’’ or ‘‘Revision 1 

date of the service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after October 3, 2012 (the effective date 

of AD 2012–15–15, Amendment 39–17144 

(77 FR 52212, August 29, 2012)). 

(2) Where Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009, specifies doing the HFEC, 

LFEC, and detailed inspections required by 

paragraph (n) of this AD before the 

accumulation of 37,500 total flight cycles, 

this AD requires the inspections to be 

accomplished at the latest of the times 

specified in paragraphs (p)(2)(i), (p)(2)(ii), 

and (p)(2)(iii) of this AD. 

(i) Before the accumulation of 37,500 total 

flight cycles. 

(ii) Within 24 months after October 3, 2012 

(the effective date of AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012)). 

(iii) Within 4,000 flight cycles since 

installation of a repair doubler; a doubler and 

a tripler; or a doubler, tripler, and 

quadrupler; or on which a preventive 

modification doubler is installed; in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–53–0094, Revision 1, 

dated August 12, 2009; or in accordance with 

paragraph (h) of this AD. 

(3) Where Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009, specifies contacting Boeing 

for repair instructions, this AD requires 

repairing in accordance with the procedures 

specified in paragraph (r) of this AD. 

(4) Where Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009, specifies a specific fastener 

and material to be used for accomplishing a 

repair, this AD allows the substitution of 

fastener and material, as specified in Chapter 

51 of the Boeing 757 Structural Repair 

Manual. 

(5) Where Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009, specifies a specific fastener 

grip length, this AD allows substitution of a 

fastener grip length, as specified in Chapter 

51 of the Boeing 757 Structural Repair 

Manual. 

(6) If it is necessary to remove more parts 

for access, those parts may be removed. If 

access is possible without removing 

identified parts, it is not necessary to remove 

all of the identified parts. 

(q) Retained Credit for Previous Actions 

This paragraph restates the credit 

provisions specified in paragraph (q) of AD 

2012–15–15, Amendment 39–17144 (77 FR 

52212, August 29, 2012). For airplanes in 

Group 1, Configurations 1 and 2; and Group 

2, Configuration 1; as defined in Boeing 

Special Attention 757–53–0094, Revision 1, 

dated August 12, 2009: This paragraph 

provides credit for the actions required by 

paragraph (k) of this AD, if those actions 

were performed before October 3, 2012 (the 

effective date of AD 2012–15–15), using 

Boeing Special Attention Service Bulletin 

757–53–0094, dated January 16, 2008; or 

Boeing Special Attention Service Bulletin 

757–53–0089, dated March 18, 2004 (which 

are not incorporated by reference in this AD). 

(r) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. 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 ACO, send it to ATTN: Nancy Marsh, 

Aerospace Engineer, Airframe Branch, ANM– 

120S, FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6440; fax: 

425–917–6432; email: nancy.marsh@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 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 previously approved in 

accordance with AD 2004–09–32, 

Amendment 39–13622 (69 FR 25481, May 7, 

2004), are approved as AMOCs for the 

corresponding actions specified in 

paragraphs (g), (h), and (i) of this AD. 

(5) AMOCs previously approved in 

accordance with AD 2012–15–15, 

Amendment 39–17144 (77 FR 52212, August 

29, 2012)), are approved as AMOCs for the 

corresponding actions specified in this AD. 

(s) Related Information 

(1) For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 1601 

Lind Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6440; fax: 425–917–6432; 

email: nancy.marsh@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, WA 98124–2207; telephone 206– 

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

Internet https://www.myboeingfleet.com. 

(t) 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. 

(3) The following service information was 

approved for IBR on October 3, 2012 (77 FR 

52212, August 29, 2012). 

(i) Boeing Special Attention Service 

Bulletin 757–53–0094, Revision 1, dated 

August 12, 2009. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on May 24, 2004 (69 FR 

25481, May 7, 2004). 

(i) Boeing Special Attention Service 

Bulletin 757–53–0089, dated March 18, 2004. 

(ii) Reserved. 

(5) 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. 

(6) You may review copies of the service 

information at the 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. 

(7) You may also review copies of the 

service information that is incorporated by 


tkelley on DSK3SPTVN1PROD with 
Federal Register / Vol. 77, No. 247 / Wednesday, December 26, 2012 / Rules and Regulations 75831 

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/ibr-locations.html. 

Issued in Renton, Washington, on 

December 5, 2012. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–30305 Filed 12–21–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1198; Directorate 

Identifier 2012–NE–35–AD; Amendment 39– 

17289; AD 2012–25–08] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

plc Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

serial numbers (S/Ns) of Rolls-Royce plc 

(RR) RB211-Trent 768–60, 772–60, and 

772B–60 turbofan engines. This AD 

requires initial and repetitive on-wing 

or in-shop inspections of the high 

pressure/intermediate pressure (HP/IP) 

turbine bearing support oil feed tube 

outer heat shield. This AD also requires 

installation of a revised HP/IP turbine 

bearing support structure as terminating 

action to the repetitive inspections of 

the HP/IP turbine bearing support oil 

feed tube outer heat shield. This AD was 

prompted by a report of high oil 

consumption due to an oil leak from the 

HP/IP turbine bearing support oil feed 

tube. We are issuing this AD to prevent 

failure of the HP turbine disc, 

uncontained engine failure, and damage 

to the airplane. 

DATES: This AD becomes effective 

January 10, 2013. 

We must receive comments on this 

AD by February 11, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication as of January 10, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications as of 

December 14, 2007 (72 FR 67568, 

November 29, 2007). 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

• Fax: 202–493–2251. 

For service information identified in 

this AD, contact Rolls-Royce plc, 

Corporate Communications, P.O. Box 

31, Derby, England, DE248BJ, phone: 

011–44–1332–242424; fax: 011–44– 

1332–245418, or email: http:// 

www.rolls-royce.com/contact/ 

civil_team.jsp. You may view this 

service information at the FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803. 

For information on the availability of 

this material at the FAA, call 781–238– 

7125. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (phone: 

800–647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Robert Morlath, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238 7154; fax: 781–238 

7199; email: robert.c.morlath@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2012– 

0201, dated September 26, 2012 

(referred to after this as ‘‘the MCAI’’), to 

correct an unsafe condition for the 

specified products. The MCAI states: 

In August 2011, a Trent 700 engine was 

removed for high oil consumption, which 

was found to have been caused by a small 

hole in the oil feed tube of the High Pressure/ 

Intermediate Pressure (HP/IP) Bearing 

Support. The hole was the result of frettage 

(chafing) with a fractured outer heat shield. 

This is a known problem and recognized 

unsafe condition that has re-emerged having 

been previously addressed by EASA AD 

2007–0260R1. 

Investigation by RR revealed a build error 

that, in contradiction to the build records, the 

previous configuration of outer heat shield 

(Pre-Service Bulletin (SB) 72–F117 standard) 

was fitted on the oil feed tube service pipe 

of the HP/IP structure. As the build error may 

have been reproduced several times, it is 

assumed that further post-SB 72–F117 

standard structures may be in service with 

pre-SB 72–F117 outer heat shields fitted to 

the oil feed tube. 

The frettage on the oil feed tube within the 

HP/IP turbine bearings support structure 

results from contact with the fracture edges 

of the tubes outermost heat shield, which has 

been found to fracture under thermal cycling 

and then to chafe against the oil tube with 

the potential to cause holes and consequent 

oil leaks. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

On November 20, 2007, we issued AD 

2007–24–09 (72 FR 67568, November 

29, 2007) which corresponds with 

EASA AD 2007–0260R1. Our AD has a 

mandatory terminating action date of 

May 31, 2010, however, there were, and 

currently are, no U.S. operators of the 

engines affected by those ADs. Those 

ADs are only applicable to engines that 

do not incorporate Modification 

Standard 72–F117. Since those ADs 

were issued, EASA has issued AD 2012– 

0201 that is applicable to a specific set 

of engines that may have had 

Modification Standard 72–F117 

incorporated incorrectly. EASA did not 

supersede EASA AD 2007–0260R1 with 

EASA AD 2012–0201 because EASA AD 

2012–0201 only affects a very specific 

population of engines that, having 

incorporated Modification Standard 72– 

F117, either correctly or incorrectly, are 

no longer affected by EASA AD 2007– 

0260R1. We are issuing our AD as a 

standalone document for the same 

reasons. This new AD also is applicable 

only to the engines specified in the 

MCAI, none of which are currently 

registered to U.S. operators. Also, this 

new AD lists certain service bulletins 

that were previously incorporated by 

reference in AD 2007–24–09. 

Relevant Service Information 

RR has issued Alert Service Bulletin 

No. RB.211–72–AG873, dated February 

27, 2012. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 


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