26720 Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 

or Airbus Service Bulletin A340–29–4091 

(for Model A340–200 and –300 series 

airplanes) has been embodied in service: 

Within 1,000 flight hours after the effective 

date of this AD, do a general visual 

inspection of the green, yellow, and blue 

high pressure manifolds and check valves 

having P/N CAR401 for any sign of rotation 

of the check valve head, and for any signs of 

hydraulic fluid leakage or seepage (including 

black deposits), in accordance with the 

instructions of Airbus Alert Operators 

Transmission A29L001–12, dated October 11, 

2012. Repeat the inspection thereafter at 

interval not to exceed 900 flight hours. 

(k) New Corrective Action for Certain 

Airplanes 

If, during any inspection required by 

paragraph (j) of this AD, any sign of rotation 

of the check valve head is found, or any sign 

of hydraulic fluid leakage or seepage 

(including black deposits) is found: Before 

further flight, do all applicable corrective 

actions, in accordance with the instructions 

of Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. 

(l) No Terminating Action 

Accomplishment of the corrective actions 

required by this AD does not constitute 

terminating action for the repetitive 

inspections required by this AD. 

(m) Replacement Check Valve Torque Value 

As of the effective date of this AD, at each 

replacement of a check valve with a check 

valve having P/N CAR401, apply a torque of 

141 to 143 newton metre (N.m) (103.98 to 

105.45 pounds-foot (lbf.ft)) during 

installation. 

(n) Credit for Previous Actions 

(1) This paragraph restates the credit 

specified in paragraph (g)(2)(iv) of AD 2009– 

24–09, Amendment 39–16068 (74 FR 62208, 

November 27, 2009). This paragraph provides 

credit for actions required by paragraph 

(g)(2)(i) of this AD, if those actions were 

performed before December 14, 2009 (the 

effective date of AD 2009–24–09), using 

Airbus AOT A330–29A3111, dated 

September 2, 2009 (for Model A330–200 and 

–300 series airplanes); or AOT A340– 

29A4086, dated September 2, 2009 (for 

Model A340–200 and –300 series airplanes). 

(2) This paragraph provides credit for 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Airbus AOT 

A330–29A3111, dated September 2, 2009; or 

Revision 1, dated October 8, 2009 (for Model 

A330–200 and –300 series airplanes); or AOT 

A340–29A4086, dated September 2, 2009; or 

Revision 1, dated October 8, 2009 (for Model 

A340–200 and –300 series airplanes). After 

the effective date of this AD all inspections 

and corrective actions, as required by 

paragraph (i) of this AD, must be 

accomplished in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A330–29–3111, 

Revision 02, dated June 23, 2011, or Airbus 

Mandatory Service Bulletin A340–29–4086, 

Revision 02, dated June 23, 2011; as 

applicable. 

(o) No Reporting 

Although the service information specified 

in paragraphs (o)(1) through (o)(5) of this AD 

specifies to submit certain information to the 

manufacturer, this AD does not include that 

requirement. 

(1) Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. 

(2) Airbus Mandatory Service Bulletin 

A330–29–3111, Revision 02, dated June 23, 

2011. 

(3) Airbus Mandatory Service Bulletin 

A340–29–4086, Revision 02, dated June 23, 

2011. 

(4) Airbus AOT A330–29A3111, Revision 

1, dated October 8, 2009. 

(5) Airbus AOT A340–29A4086, Revision 

1, dated October 8, 2009. 

(p) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, Transport Airplane Directorate, 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 International Branch, send it 

to ATTN: Vladimir Ulyanov, Aerospace 

Engineer, International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 1601 

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

telephone 425–227–1138; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 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. The AMOC approval letter 

must specifically reference this AD. AMOCs 

approved for AD 2009–24–09, Amendment 

39–16068 (74 FR 62208, November 27, 2009) 

are approved as AMOCs for the 

corresponding provisions of this AD, except 

AMOC ANM–116–11–172 is not approved as 

an AMOC for the corresponding provisions of 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(q) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information European 

Aviation Safety Agency Airworthiness 

Directive 2012–0244R1, dated January 25, 

2013; and the following service information; 

for related information. 

(i) Airbus Alert Operators Transmission 

A29L001–12, dated October 11, 2012. 

(ii) Airbus Mandatory Service Bulletin 

A330–29–3111, Revision 02, dated June 23, 

2011. 

(iii) Airbus Mandatory Service Bulletin 

A340–29–4086, Revision 02, dated June 23, 

2011. 

(iv) Airbus AOT A330–29A3111, Revision 

1, dated October 8, 2009. 

(v) Airbus AOT A340–29A4086, Revision 

1, dated October 8, 2009. 

(2) For service information identified in 

this AD, contact, Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

5 61 93 36 96; fax +33 5 61 93 45 80; email 

airworthiness.A330–A340@airbus.com; 

Internet http://www.airbus.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. 

Issued in Renton, Washington, on April 26, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–10908 Filed 5–7–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0366; Directorate 

Identifier 2011–NM–024–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–300, 747–400, 747–400D, and 

747SR series airplanes. The existing AD 

requires, for certain airplanes, 

inspection to determine the material of 

a main entry door (MED) reveal; 

repetitive inspections of certain reveals 

for cracking; a detailed inspection of 

certain reveals for a sharp edge and 

cracking; and corrective action if 

necessary. That AD also allows a certain 

replacement as an optional action for 

certain inspections of certain airplanes. 

Since we issued that AD, an operator 

reported a crack found in a 6061 

machined aluminum one-piece corner 

reveal. This proposed AD would add, 

for certain airplanes, an inspection to 

determine material type of MED reveals, 

repetitive inspections for cracking of 

6061 machined aluminum one-piece 

corner reveals, and replacement with 

6061 machined aluminum two-piece 

corner reveals if necessary. This 

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Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 26721 

proposed AD would also allow 

replacement with two-piece corner 

reveals as an option for certain 

repetitive inspections. This proposed 

AD would also revise the applicability 

by removing a certain airplane. We are 

proposing this AD to detect and correct 

fatigue cracking of the lower forward 

corner reveal of the number 3 MEDs, 

which could lead to the door escape 

slide departing the airplane when the 

door is opened and the slide is 

deployed, and consequent injuries to 

passengers and crew using the door 

escape slide during an emergency 

evacuation. 

DATES: We must receive comments on 

this proposed AD by June 24, 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: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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 proposed 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: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: (425) 917–6432; fax: (425) 

917–6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0366; Directorate Identifier 

2011–NM–024–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 proposed AD. 

Discussion 

On August 20, 2008, we issued AD 

2008–18–07, Amendment 39–15664 (73 

FR 56960, October 1, 2008), for certain 

The Boeing Company Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–300, 747–400, 747– 

400D, and 747SR series airplanes. The 

existing AD requires, for certain 

airplanes, an inspection to determine 

the material of an MED reveal; repetitive 

inspections of certain reveals for 

cracking; a detailed inspection of certain 

reveals for a sharp edge and cracking; 

and corrective action if necessary. That 

AD also allows a certain replacement as 

an optional action for certain 

inspections of certain airplanes. The 

existing AD resulted from reports of 

cracking and/or a sharp edge in the 

lower forward corner reveal of the 

number 3 MEDs. We issued that AD to 

detect and correct fatigue cracking of the 

lower forward corner reveal of the 

number 3 MEDs, which could lead to 

the door escape slide departing the 

airplane when the door is opened and 

the slide is deployed, and possible 

consequent injuries to passengers and 

crew using the door escape slide during 

an emergency evacuation. 

Actions Since Existing AD (73 FR 

56960, October 1, 2008) Was Issued 

Since we issued AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, 

October 1, 2008), an operator reported a 

crack found in a 6061 machined 

aluminum one-piece corner reveal. 

Certain airplanes were equipped with 

either 356 cast aluminum or 6061 

machined aluminum one-piece corner 

reveals at delivery. The existing AD 

allowed 356 cast aluminum reveals to 

be replaced with one-piece machined 

aluminum corner reveals. We have 

determined that inspections are 

necessary on airplanes having these 

one-piece reveals. 

Relevant Service Information 

AD 2008–18–07, Amendment 39– 

15664 (73 FR 56960, October 1, 2008), 

referred to Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 

1, dated February 13, 2007, as the 

appropriate source of service 

information for the required actions. 

Boeing has since revised this service 

information. 

We reviewed Boeing Special 

Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 

2010. No new airplanes were added to 

the effectivity of Boeing Special 

Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 

2010, but airplane groups were changed 

based on the material composition of 

the corner reveals. This service 

information describes procedures for a 

material type inspection of one-piece or 

two-piece corner reveals; inspection for 

sharp edges and cracking; and 

replacement of reworked 356 cast 

aluminum corner reveals and 6061 

machined aluminum one-piece corner 

reveals with 6061 machined aluminum 

two-piece corner reveals, which would 

eliminate the need for repetitive 

inspections. 

Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, also specifies a 

revised effectivity that clarifies the cargo 

configuration exceptions by excluding 

airplanes modified to the Boeing 

converted freighter and large cargo 

freighter configurations and removing 

an exception for Groups 2 and 3 of 

airplanes modified to the special 

freighter configuration. This service 

information also removes line number 

(L/N) 1271, a Model 747–400F series 

airplane, from the effectivity because it 

is a freighter airplane. 

FAA’s Determination 

We are proposing 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. 

Proposed AD Requirements 

This proposed AD would retain all of 

the requirements of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, 

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26722 Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 

October 1, 2008). The proposed AD 

would require the actions specified in 

the service information described 

previously. The proposed AD would 

add, for certain airplanes, an inspection 

to determine material type of MED 

reveals, repetitive inspections for 

cracking of 6061 machined aluminum 

one-piece corner reveals, and 

replacement with 6061 machined 

aluminum two-piece corner reveals if 

necessary. This proposed AD would 

also allow replacement with two-piece 

corner reveals as an option for certain 

repetitive inspections. Also, the 

proposed AD would remove airplane L/ 

N 1271, a Model 747–400F series 

airplane, from the AD applicability. 

Changes To Existing AD (73 FR 56960, 

October 1, 2008) 

This proposed AD would retain all of 

the requirements of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, 

October 1, 2008). However, we have 

removed the ‘‘Service Bulletin 

Reference’’ paragraph from this 

proposed AD. That paragraph was 

identified as paragraph (f) in AD 2008– 

18–07. That paragraph provided 

operators with a one-time citation of the 

referenced service bulletin in AD 2008– 

18–07. Instead, we have provided the 

full service bulletin citation throughout 

this proposed AD. 

We have revised the heading and 

wording for paragraph (l) of this 

proposed AD, to clarify that the only 

exception to the procedures in Boeing 

Special Attention Service Bulletin 747– 

53–2460, Revision 1, dated February 13, 

2007; and Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 

2, dated December 22, 2010; is that, as 

of the effective date of this proposed 

AD, an operator’s equivalent procedure 

may no longer be used without 

requesting approval of an alternative 

method of compliance (AMOC). 

We have also re-designated Notes 1 

and 2 of AD 2008–18–07, Amendment 

39–15664 (73 FR 56960, October 1, 

2008), as paragraphs (p) and (q) of this 

proposed AD. This change does not 

affect the intent of those paragraphs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 166 airplanes of U.S. registry. We 

estimate the following costs to comply 

with this proposed AD: 

ESTIMATED COSTS

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

Material type inspection and inspection for cracks 

(retained actions from AD 2008–18–07, 

Amendment 39-15664 (73 FR 56960, October 

1, 2008)) (119 airplanes).

4 work-hours × $85 per 

hour = $340 per inspection cycle.

$0 $340 per inspection 

cycle.

$40,460 per inspection 

cycle. 

New Material type inspection and inspection for 

cracks [new proposed action] (166 airplanes).

14 work-hours × $85 

per hour = $1,190 per 

inspection cycle.

$0 $1,190 per inspection 

cycle.

$197,540 per inspection 

cycle. 

We estimate the following costs to do 

any necessary on-condition actions that 

would be required based on the results 

of the proposed inspections. We have no 

way of determining the number of 

aircraft that might need these actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Corner reveal removal and replacement [new proposed action].17 work-hours × $85 per hour = 

$1,445 per inspection cycle.

$9,525 $10,970 per inspection cycle. 

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 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would 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 the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. 

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Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 26723 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2008–18–07, Amendment 39–15664 (73 

FR 56960, October 1, 2008), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2013–0366; Directorate Identifier 2011– 

NM–024–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by June 24, 2013. 

(b) Affected ADs 

This AD supersedes AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–300, 747–400, 

747–400D, and 747SR series airplanes, 

certificated in any category, as identified in 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010, except airplanes that have been 

converted to an all-cargo configuration. The 

requirements of this AD also become 

applicable at the time when a converted 

airplane operating in an all-cargo 

configuration is converted back to a 

passenger or passenger/cargo configuration. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53: Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

crack found in a 6061 machined aluminum 

one-piece corner reveal. We are proposing 

this AD to detect and correct fatigue cracking 

of the lower forward corner reveal of the 

number 3 main entry doors (MEDs), which 

could lead to the door escape slide departing 

the airplane when the door is opened and the 

slide is deployed, and consequent injuries to 

passengers and crew using the door escape 

slide during an emergency evacuation. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Actions for Group 3 Airplanes 

This paragraph restates the requirements of 

paragraph (g) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), with revised service information. 

For airplanes identified as Group 3 airplanes 

in Boeing Special Attention Service Bulletin 

747–53–2460, Revision 1, dated February 13, 

2007: Before the accumulation of 10,000 total 

flight cycles, or within 1,000 flight cycles 

after November 5, 2008 (the effective date of 

AD 2008–18–07), whichever occurs later, do 

a detailed inspection for cracking of the 

lower forward corner reveals, in accordance 

with Part 8 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; or Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

As of the effective date of this AD, only 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010, may be used to accomplish the 

actions required by this paragraph. 

(1) If no cracking is found, repeat the 

inspection thereafter at intervals not to 

exceed 6,000 flight cycles until a new or 

reworked two-piece reveal is installed in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. As of the effective date of this AD, 

only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. No further action is required by 

this paragraph for that location only after the 

replacement. 

(2) If cracking is found, do the replacement 

specified in paragraph (g)(2)(i) or (g)(2)(ii) of 

this AD. 

(i) Before further flight, replace the reveal 

with a new or reworked two-piece reveal, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. No further action is required by this 

paragraph for that location only after the 

replacement. As of the effective date of this 

AD, only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(ii) Before further flight, replace the reveal 

with a new or reworked one-piece machined 

aluminum reveal without a sharp edge, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 4 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Before the accumulation of 10,000 

flight cycles since new on the replacement 

reveal, do the inspection for cracking 

specified in Part 8 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; or Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

Repeat the inspection thereafter at intervals 

not to exceed 6,000 flight cycles until a new 

or reworked two-piece reveal is installed in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. If any cracking is found during any 

inspection required by this paragraph, before 

further flight, do the actions specified in 

paragraph (g)(2) of this AD. No further action 

is required by this paragraph for that location 

only after the replacement with a two-piece 

reveal. As of the effective date of this AD, 

only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(h) Retained Actions for Group 2 Airplanes 

This paragraph restates the requirements of 

paragraph (h) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), with revised service information. 

For airplanes identified as Group 2 airplanes 

in Boeing Special Attention Service Bulletin 

747–53–2460, Revision 1, dated February 13, 

2007; or Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010: Before the accumulation 

of 1,500 total flight cycles, or within 1,000 

flight cycles after November 5, 2008 (the 

effective date of AD 2008–18–07), whichever 

occurs later, do the inspection specified in 

paragraph (j) of this AD. 

(i) Retained Actions for Group 1, 

Configuration 2 Airplanes 

This paragraph restates the requirements of 

paragraph (i) of AD 2008–18–07, Amendment 

39–15664 (73 FR 56960, October 1, 2008), 

with revised service information. For 

airplanes identified as Group 1, 

Configuration 2 airplanes in Boeing Special 

Attention Service Bulletin 747–53–2460, 

Revision 1, dated February 13, 2007; or 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010: Within 1,500 flight cycles after the 

lower forward corner reveal was last 

replaced, or 1,000 flight cycles after 

November 5, 2008 (the effective date of AD 

2008–18–07), whichever occurs later, do the 

inspection specified in paragraph (j) of this 

AD. 

(j) Retained Inspection for Cracking and 

Sharp Edge 

This paragraph restates the requirements of 

paragraph (j) of AD 2008–18–07, Amendment 

39–15664 (73 FR 56960, October 1, 2008), 

with revised service information. At the 

applicable times specified in paragraphs (h) 

and (i) of this AD: Do a detailed inspection 

of the lower forward corner reveal for 

cracking and a sharp edge, in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; or Part 1 and Part 

2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. As of the effective date of this AD, 

only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(1) If no cracking and no sharp edge are 

found, before the accumulation of 10,000 

flight cycles on the lower forward corner 

reveal since new, or within 6,000 flight 

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cycles after doing the inspection required by 

paragraph (j) of this AD, whichever occurs 

later, do a detailed inspection for cracking, in 

accordance with Part 8 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Inspect thereafter at intervals not to 

exceed 6,000 flight cycles, until a new or 

reworked two-piece reveal is installed in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. If any cracking is found during any 

inspection required by this paragraph, before 

further flight, do the actions specified in 

paragraph (j)(3) of this AD. No further action 

is required by this paragraph for that location 

only after the replacement with a two-piece 

reveal. As of the effective date of this AD, 

only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(2) If no cracking is found, but a sharp edge 

is found, do the actions specified in 

paragraph (j)(2)(i) or (j)(2)(ii) of this AD. 

(i) Before further flight, replace the lower 

forward corner reveal with a new or 

reworked two-piece reveal, in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; or Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

No further action is required by this 

paragraph for that location only after the 

replacement. As of the effective date of this 

AD, only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(ii) Before further flight, replace the reveal 

with a new or reworked one-piece machined 

aluminum reveal without a sharp edge, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 4 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Before the accumulation of 10,000 

flight cycles on the replacement reveal since 

new, do the inspection for cracking, in 

accordance with Part 8 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Inspect thereafter at intervals not to 

exceed 6,000 flight cycles, until a new or 

reworked two-piece reveal is installed in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. If any cracking is found during any 

inspection required by this paragraph, before 

further flight, do the actions specified in 

paragraph (j)(3) of this AD. No further action 

is required by this paragraph for that location 

only after the replacement with a two-piece 

reveal. As of the effective date of this AD, 

only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(3) If cracking is found, do the actions 

specified in paragraph (j)(3)(i) or (j)(3)(ii) of 

this AD. 

(i) Before further flight, replace the reveal 

with a new or reworked two-piece reveal, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. No further action is required by this 

paragraph for that location only after the 

replacement. As of the effective date of this 

AD, only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(ii) Before further flight, replace the lower 

forward corner reveal with a new or 

reworked one-piece machined aluminum 

reveal without a sharp edge, in accordance 

with Part 3 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; or Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

Before the accumulation of 10,000 flight 

cycles since new on the replacement reveal, 

do the inspection for cracking, in accordance 

with Part 8 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; or Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

Inspect thereafter at intervals not to exceed 

6,000 flight cycles, until a new or reworked 

two-piece reveal is installed in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; or Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

If any cracking is found during any 

inspection required by this paragraph, before 

further flight, do the actions required by 

paragraph (j)(3) of this AD. No further action 

is required by this paragraph for that location 

only after the replacement with a two-piece 

reveal. As of the effective date of this AD, 

only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(k) Retained Actions for Group 1, 

Configuration 1 Airplanes 

This paragraph restates the requirements of 

paragraph (k) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), with revised service information. 

For airplanes identified as Group 1, 

Configuration 1 airplanes in Boeing Special 

Attention Service Bulletin 747–53–2460, 

Revision 1, dated February 13, 2007: Before 

the accumulation of 1,500 total flight cycles, 

or within 1,000 flight cycles after November 

5, 2008 (the effective date of AD 2008–18– 

07), whichever occurs later, do a material 

type inspection to determine if the lower 

forward corner reveals are castings, in 

accordance with Part 1 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 6 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. As an alternative to the material 

type inspection, replacing a reveal with a 

new or reworked two-piece lower forward 

corner reveal, in accordance with Part 2 of 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010; is terminating action for the 

requirements of this paragraph for that 

location only. As of the effective date of this 

AD, only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(1) If the forward corner reveal is not a 

casting: Before further flight, do the actions 

specified in paragraph (j) of this AD except 

for the inspection for a sharp edge. 

(2) If the forward corner reveal is a casting: 

Before the accumulation of 7,000 total flight 

cycles, within 2,000 flight cycles after 

November 5, 2008 (the effective date of AD 

2008–18–07), or within 3,000 flight cycles 

since the forward corner reveal was 

inspected as specified in Boeing Service 

Bulletin 747–53A2378, Revision 3, dated 

August 11, 2005; or Boeing Service Bulletin 

747–53A2378, Revision 4, dated June 10, 

2010; whichever occurs latest; do a detailed 

inspection for cracking of the lower forward 

corner reveal, in accordance with Part 1 of 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. As of the effective date of this AD, 

only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

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(i) If no cracking is found: Repeat the 

inspection specified in paragraph (k)(2) of 

this AD thereafter at intervals not to exceed 

3,000 flight cycles until a new or reworked 

two-piece lower forward corner reveal is 

installed in accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. No further action is required by this 

paragraph for that location only after the 

replacement. 

(ii) If cracking is found: Do the actions 

specified in paragraph (k)(2)(ii)(A), 

(k)(2)(ii)(B), or (k)(2)(ii)(C) of this AD. 

(A) Before further flight, weld repair the 

reveal, in accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 4 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Repeat the inspection specified in 

paragraph (k)(2) of this AD thereafter at 

intervals not to exceed 3,000 flight cycles 

until a new or reworked two-piece reveal is 

installed in accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. No further action is required by this 

paragraph for that location only after the 

replacement. As of the effective date of this 

AD, only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(B) Before further flight, replace the reveal 

with a new or reworked two-piece reveal, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. No further action is required by this 

paragraph for that location only after the 

replacement. As of the effective date of this 

AD, only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(C) Before further flight, replace the reveal 

with a new or reworked one-piece machined 

aluminum reveal without a sharp edge, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 4 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Before the accumulation of 10,000 

flight cycles since new on the replacement 

reveal, do the inspection for cracking, in 

accordance with Part 8 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Inspect thereafter at intervals not to 

exceed 6,000 flight cycles, until a new or 

reworked two-piece reveal is installed in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. If any cracking is found during any 

inspection required by this paragraph, before 

further flight, do the actions specified in 

paragraph (k)(2)(ii)(B) or (k)(2)(ii)(C) of this 

AD. No further action is required by this 

paragraph for that location only after the 

replacement with a two-piece reveal. As of 

the effective date of this AD, only Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010, 

may be used to accomplish the actions 

required by this paragraph. 

(l) Retained Requirement Regarding 

Operator’s Equivalent Procedure 

This paragraph restates the requirements of 

paragraph (l) of AD 2008–18–07, Amendment 

39–15664 (73 FR 56960, October 1, 2008). 

Although Step 5 of Figure 8 of Boeing Special 

Attention Service Bulletin 747–53–2460, 

Revision 1, dated February 13, 2007, 

specifies that operators may accomplish the 

actions in accordance with ‘‘an operator’s 

equivalent procedure,’’ this AD does not 

allow using an ‘‘operator equivalent 

procedure unless approved as an alternative 

method of compliance in accordance with 

paragraph (w) of this AD. 

(m) Retained Provisions for Compliance 

With AD 2007–12–11, Amendment 39–15089 

(72 FR 31984, June 11, 2007), for MED 3 

Only 

This paragraph restates the provisions of 

paragraph (m) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), with revised information. 

Accomplishment of the applicable repair 

required by AD 2008–18–07, Amendment 

39–15664 (73 FR 56960, October 1, 2008), 

constitutes compliance with the repair of the 

lower forward corner casting (reveal) of the 

number 3 MEDs only, as required by 

paragraph (q)(2)(ii) of AD 2007–12–11, 

Amendment 39–15089 (72 FR 31984, June 

11, 2007), which specifies the actions must 

be done in accordance with Boeing Service 

Bulletin 747–53A2378, Revision 1, dated 

March 10, 1994; Boeing Service Bulletin 747– 

53A2378, Revision 3, dated August 11, 2005; 

or Boeing Service Bulletin 747–53A2378, 

Revision 4, dated June 10, 2010. As of the 

effective date of this AD, only Boeing Service 

Bulletin 747–53A2378, Revision 4, dated 

June 10, 2010, may be used to accomplish the 

actions specified in this paragraph. 

Accomplishment of the actions of this AD 

does not terminate the remaining 

requirements of AD 2007–12–11. 

(n) Retained Parts Installation Prohibition 

(Cast 356 Aluminum) Reveals 

This paragraph restates the requirement of 

paragraph (n) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008). As of November 5, 2008 (the 

effective date of AD 2008–18–07), no person 

may install a door lower forward corner 

reveal made of cast 356 aluminum on any 

airplane at a location specified by AD 2008– 

18–07. 

(o) Retained Parts Installation Limitation 

(Machined 6061 Aluminum) Reveals 

This paragraph restates the limitation 

specified by paragraph (o) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), with revised service information. As 

of November 5, 2008 (the effective date of AD 

2008–18–17), no person may install a door 

lower forward corner reveal made of 

machined 6061 aluminum on any airplane at 

a location specified by this AD, unless it has 

been confirmed/reworked to be without a 

sharp edge, in accordance with Part 5 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 1 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. As of the effective date of this AD, 

only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(p) Retained Optional Rework of One-Piece 

and Two-Piece Machined 6061 Aluminum 

Reveals 

This paragraph restates the information 

provided in ‘‘Note 1’’ of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), with revised information. For the 

purpose of this AD, a one-piece machined 

6061 aluminum reveal may be reworked into 

a two-piece reveal in accordance with the 

Accomplishment Instructions of the 

applicable service bulletin identified in 

paragraph of (p)(1) or (p)(2) of this AD, after 

it was verified to be crack free and without 

a sharp edge, or after it was confirmed to be 

crack free and reworked to remove a sharp 

edge. As of the effective date of this AD, only 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010, may be used to accomplish the 

actions provided by this paragraph. 

(1) Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 1, dated 

February 13, 2007. 

(2) Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010. 

(q) Retained Optional Rework of One-Piece 

6061 Aluminum Reveals With a Sharp Edge 

This paragraph restates the information 

provided in ‘‘Note 2’’ of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), with revised service information. 

For the purpose of this AD, a one-piece 

machined 6061 aluminum reveal with a 

sharp edge may be reworked into a one-piece 

machined 6061 aluminum reveal without a 

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sharp edge, in accordance with Part 6 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 1 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010; after it is confirmed to be crack free 

in accordance with Part 5 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007, or 

Part 2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. After the sharp edge is removed, 

the one-piece machined 6061 aluminum 

reveal without a sharp edge may be further 

reworked into a two-piece reveal, in 

accordance with Part 7 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Part 5 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. As of the effective date of this AD, 

only Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, may be used to 

accomplish the actions specified by this 

paragraph. 

(r) New Actions for Previously Inspected 

Group 4 Airplanes: Corner Reveal Not 

Replaced, or Replaced With Two-Piece 

Reveal 

For Group 4 airplanes identified in Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010, 

that have been inspected previously in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; and on which the 

corner reveal either has not been replaced, or 

has been replaced with a two-piece reveal 

that was made by reworking an existing onepiece reveal: Before the accumulation of 

7,000 total flight cycles, or within 3,000 flight 

cycles after the most recent inspection or 

rework done in accordance with Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 1, dated February 13, 2007; or 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010; or within 1,000 flight cycles after 

the effective date of this AD, whichever 

occurs latest; do a material type inspection to 

determine if the corner reveal is a casting, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

Doing the inspection specified in this 

paragraph terminates the inspections 

required by paragraph (j) of this AD for these 

airplanes. 

(1) If, during any inspection required by 

paragraph (r) of this AD, any corner reveal is 

found to be a casting: Before further flight, do 

a detailed inspection for cracking of the 

corner reveal, in accordance with Part 2 of 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010; 

and repeat the inspection thereafter at 

intervals not to exceed 3,000 flight cycles 

until a new two-piece reveal in installed in 

accordance with the requirements of 

paragraph (r)(1)(i) of this AD. If any cracking 

is found, do the actions specified in 

paragraph (r)(1)(i) or (r)(1)(ii) of this AD. 

(i) Replace the cast reveal with a new 6061 

machined aluminum two-piece corner reveal, 

before further flight, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. 

(ii) Repair all cracking, before further 

flight, in accordance with Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

(2) If, during any inspection required by 

paragraph (r) of this AD, any one-piece 

corner reveal is found to be installed and is 

not a casting: Before the accumulation of 

10,000 total flight cycles; or within 6,000 

flight cycles after the most recent inspection 

done in accordance with Boeing Special 

Attention Service Bulletin 747–53–2460, 

Revision 1, dated February 13, 2007; or 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010; whichever occurs later; do a 

detailed inspection of the corner reveal for 

cracking, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

Repeat the inspection for cracking thereafter 

at intervals not to exceed 6,000 flight cycles 

until the corner reveal is replaced with a 

6061 machined aluminum two-piece corner 

reveal. If any cracking is found during any 

inspection required by paragraph (r)(2) of this 

AD, before further flight, replace the corner 

reveal with a 6061 machined aluminum twopiece corner reveal, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. 

(s) New Actions for Previously Inspected 

Group 4 Airplanes: Corner Reveal Replaced 

With One-Piece Reveal 

For Group 4 airplanes identified in Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010, 

that have been inspected previously in 

accordance with Boeing Service Bulletin 

747–53–2460, Revision 1, dated February 13, 

2007, and on which the corner reveal has 

been replaced with a one-piece reveal: 

Within 10,000 flight cycles after the date the 

reveal was replaced with a one-piece corner 

reveal, do a detailed inspection for cracking 

of the corner reveal, in accordance with Part 

2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Repeat the inspection for cracking 

thereafter at intervals not to exceed 6,000 

flight cycles until the corner reveal is 

replaced with a 6061 machined aluminum 

two-piece corner reveal, in accordance with 

the requirements of paragraph (u) of this AD. 

If any cracking is found during any 

inspection required this paragraph of this 

AD, before further flight, replace the onepiece corner reveal with a 6061 machined 

aluminum two-piece corner reveal, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

(t) New Actions for Group 4 Airplanes: Not 

Previously Inspected or Changed 

For Group 4 airplanes identified in Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010, 

that have not been previously inspected or 

changed in accordance with Boeing Special 

Attention Service Bulletin 747–53–2460, 

Revision 1, dated February 13, 2007: Before 

the accumulation of 1,500 total flight cycles, 

or within 1,000 flight cycles after the 

effective date of this AD, whichever occurs 

later, do a material type inspection to 

determine if the lower forward corner reveal 

is made from 6061 machined aluminum plate 

or 356 aluminum casting, in accordance with 

Part 6 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Doing the inspection specified in 

this paragraph terminates the inspections 

required by paragraph (j) of this AD for these 

airplanes. 

(1) If, during any inspection required by 

paragraph (t) of this AD, any corner reveal is 

found to be a casting: Before the 

accumulation of 7,000 total flight cycles; or 

within 2,000 flight cycles after the effective 

date of this AD; or within 3,000 flight cycles 

after the most recent inspection of the MED 

3 corner reveal was done in accordance with 

Boeing Service Bulletin 747–53A2378, 

Revision 4, dated June 10, 2010; whichever 

occurs latest; do a detailed inspection for 

cracking of the corner reveal, in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 2, 

dated December 22, 2010. Repeat the 

inspection for cracking thereafter at intervals 

not to exceed 3,000 flight cycles until the 

corner reveal is replaced with a 6061 

machined aluminum two-piece corner reveal. 

If any cracking is found during any 

inspection required by this paragraph of this 

AD, before further flight, replace the casting 

with a 6061 machined aluminum two-piece 

corner reveal, in accordance with Part 3 of 

the Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

(2) If, during any inspection required by 

paragraph (t) of this AD, a corner reveal is 

found that is not a casting: Before further 

flight, do a detailed inspection for a sharp 

edge, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010; 

and do a detailed inspection for cracking of 

the corner reveal, in accordance with Part 2 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Repeat the inspection for cracking 

thereafter at intervals not to exceed 6,000 

flight cycles until the corner reveal is 

replaced with a 6061 machined aluminum 

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Federal Register / Vol. 78, No. 89 / Wednesday, May 8, 2013 / Proposed Rules 26727 

two-piece corner reveal in accordance with 

the requirements of paragraph (u) of this AD. 

(i) If any sharp edge is found during any 

inspection required by paragraph (t)(2) of this 

AD, before further flight, rework the corner 

reveal, in accordance with Part 1 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

(ii) If any cracking is found during any 

inspection required by paragraph (t)(2) of this 

AD, before further flight, replace the corner 

reveal with a 6061 machined aluminum twopiece corner reveal, in accordance with Part 

3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. 

(u) New Terminating Action for Repetitive 

Inspections 

Installation of a 6061 machined aluminum 

two-piece corner reveal in accordance with 

Part 3 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010, terminates the repetitive 

inspections required by paragraphs (r), (s), 

and (t) of this AD. 

(v) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraphs (g) through (m) and 

(o) through (q) of this AD, if those actions 

were performed before the effective date of 

this AD using Boeing Special Attention 

Service Bulletin 747–53–2460, Revision 1, 

dated February 13, 2007; or Boeing Service 

Bulletin 747–53A2378, Revision 3, dated 

August 11, 2005; as applicable, which are not 

incorporated by reference in this AD. 

(w) 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. 

(4) AMOCs previously approved in 

accordance with AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), are approved as AMOCs for the 

corresponding requirements of this AD for 

Group 2 and Group 3 airplanes identified in 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. Previously approved AMOCs for 

Group 1 and Group 4 airplanes identified in 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010, are not approved for compliance 

with the actions required by this AD. 

(x) 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, WA 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. 

Issued in Renton, Washington, on April 26, 

2013. 

Ali Bahrami, 

Manager, Transport Aircraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–10905 Filed 5–7–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Employee Benefits Security 

Administration 

29 CFR Part 2520 

RIN 1210–AB20 

Pension Benefit Statements 

AGENCY: Employee Benefits Security 

Administration, Department of Labor. 

ACTION: Advance notice of proposed 

rulemaking. 

SUMMARY: The Department of Labor 

(Department) is developing proposed 

regulations regarding the pension 

benefit statement requirements under 

section 105 of the Employee Retirement 

Income Security Act of 1974, as 

amended (ERISA). This advance notice 

of proposed rulemaking (ANPRM) 

describes certain rules the Department 

is considering as part of the proposed 

regulations. The rules being considered 

are limited to the pension benefit 

statements required of defined 

contribution plans. First, the 

Department is considering a rule that 

would require a participant’s accrued 

benefits to be expressed on his pension 

benefit statement as an estimated 

lifetime stream of payments, in addition 

to being presented as an account 

balance. Second, the Department also is 

considering a rule that would require a 

participant’s accrued benefits to be 

projected to his retirement date and 

then converted to and expressed as an 

estimated lifetime stream of payments. 

This ANPRM serves as a request for 

comments on specific language and 

concepts in advance of proposed 

regulations. The Department intends to 

consider all reasonable alternatives to 

direct regulation, including whether 

there is a way short of a regulatory 

mandate that will ensure that 

participants and beneficiaries get 

constructive and helpful lifetime 

income illustrations. 

DATES: Comments are due on or before 

July 8, 2013. 

ADDRESSES: You may submit comments, 

identified by RIN 1210–AB20, by one of 

the following methods: 

• Federal eRulemaking Portal: http:// 

www.regulations.gov. Follow the 

instructions for submitting comments. 

• Email: e-ORI@dol.gov. Include RIN 

1210–AB20 in the subject line of the 

message. 

• Mail: Office of Regulations and 

Interpretations, Employee Benefits 

Security Administration, Room N–5655, 

U.S. Department of Labor, 200 

Constitution Avenue NW., Washington, 

DC 20210, Attention: Pension Benefit 

Statements Project. 

Instructions: All submissions received 

must include the agency name and 

Regulation Identifier Number (RIN) for 

this rulemaking. Comments received 

will be posted without change to 

http://www.regulations.gov and http:// 

www.dol.gov/ebsa, and made available 

for public inspection at the Public 

Disclosure Room, N–1513, Employee 

Benefits Security Administration, 200 

Constitution Avenue NW., Washington, 

DC 20210, including any personal 

information provided. Persons 

submitting comments electronically are 

encouraged not to submit paper copies. 

FOR FURTHER INFORMATION CONTACT: 

Suzanne Adelman or Tom Hindmarch at 

(202) 693–8500. This is not a toll free 

number. 

SUPPLEMENTARY INFORMATION: This 

ANPRM has two main sections followed 

by Appendix A. The first section, 

entitled ‘‘Background,’’ contains the 

relevant statutory language on which 

the Department is basing the ANPRM 

and a discussion of the Department’s 

general policy concern underlying the 

ANPRM. The second section, entitled 

‘‘Overview of Intended Regulations,’’ 

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