This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

81879 

Vol. 76, No. 250 

Thursday, December 29, 2011 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0794; Directorate 

Identifier 2009–NM–035–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (NPRM); 

reopening of comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for all The Boeing Company Model 747– 

100, 747–100B, 747–100B SUD, 747– 

200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, 

and 747SP series airplanes. The original 

NPRM proposed a general visual 

inspection to identify any existing 

structural repair manual repairs of the 

upper main sill outer chord of the left 

and right side main entry door number 

1, as applicable; repetitive detailed 

inspections for cracks in the upper main 

sill of the door(s); and related 

investigative and corrective actions, if 

necessary. The original NPRM also 

proposed repetitive inspections for 

airplanes on which a certain repair is 

done, and corrective actions if 

necessary. The original NPRM was 

prompted by reports of cracks in the 

main entry door number 1 upper main 

sill outer chord, along the bend radius 

of the chord on several airplanes. This 

action revises the original NPRM by 

reducing certain compliance times. We 

are proposing this supplemental NPRM 

to detect and correct cracks in the main 

entry door number 1 upper main sill 

outer chord, along the bend radius of 

the chord, which could result in loss of 

structural integrity of the airplane. Since 

these actions impose an additional 

burden over that proposed in the 

original NPRM, we are reopening the 

comment period to allow the public the 

chance to comment on these proposed 

changes. 

DATES: We must receive comments on 

this supplemental NPRM by February 

13, 2012. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, 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 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; email 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call (425) 227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

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

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: Ivan 

Li, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6437; 

fax: (425) 917–6590; email: 

ivan.li@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–2009–0794; Directorate Identifier 

2009–NM–035–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 

We issued a notice of proposed 

rulemaking (NPRM) (the ‘‘original 

NPRM’’) to amend 14 CFR part 39 to 

include an airworthiness directive (AD) 

that would apply to all The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747– 

400D, 747–400F, 747SR, and 747SP 

series airplanes. That original NPRM 

was published in the Federal Register 

on September 28, 2009 (74 FR 49351). 

That original NPRM proposed to require 

a general visual inspection to identify 

any existing structural repair manual 

(SRM) repairs of the upper main sill 

outer chord of the left and right side 

main entry door number 1, as 

applicable; repetitive detailed 

inspections for cracks in the upper main 

sill of the door(s); and related 

investigative and corrective actions, if 

necessary. The original NPRM also 

proposed to require repetitive 

inspections for airplanes on which a 

certain repair is done, and corrective 

actions if necessary. 


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81880 Federal Register / Vol. 76, No. 250 / Thursday, December 29, 2011 / Proposed Rules 

Actions Since Previous NPRM Was 

Issued 

Since we issued the original NPRM 

(74 FR 49351, September 28, 2009), 

Boeing has issued Boeing Alert Service 

Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. Among other 

things, Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010, makes certain grouping changes 

for the affected airplanes, and also 

describes procedures for reducing the 

compliance threshold and repetitive 

interval for inspections of Model 747– 

400 series airplanes modified to the 

large cargo freighter (LCF) configuration. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received from 

the commenters. 

Request To Change Compliance Times 

for Certain Airplanes 

Boeing requested that we revise 

paragraphs (g), (h)(1), and (i) of the 

original NPRM (74 FR 49351, September 

28, 2009) to reduce the compliance 

times and repetitive inspection interval 

for certain Model 747–400 series 

airplanes modified to the LCF 

configuration. Boeing explained that 

those airplanes operate at higher stress 

levels, and that cracks may initiate 

sooner and grow faster. Boeing 

suggested using the compliance times in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, instead 

of the compliance times listed in 

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

Alert Service Bulletin 747–53A2785, 

dated February 12, 2009, which was 

referred to in the original NPRM. 

We agree to revise this supplemental 

NPRM as requested by the commenter. 

The original NPRM (74 FR 49351, 

September 28, 2009) referred to Boeing 

Alert Service Bulletin 747–53A2785, 

dated February 12, 2009, as the 

appropriate source of service 

information. We have reviewed Boeing 

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010. Among 

other things, this service information 

makes certain grouping changes for the 

affected airplanes. This service 

information also describes procedures 

for reducing the compliance threshold 

and repetitive interval for inspections of 

Model 747–400 series airplanes 

modified to the LCF configuration. This 

service information specifies that the 

reduced compliance threshold for those 

airplanes is 10,000 total flight cycles or 

within 1,500 flight cycles after the date 

of Boeing Alert Service Bulletin 747– 

53A2785, Revision 1, dated July 15, 

2010 (whichever occurs later). The 

revised repetitive interval for those 

airplanes is 3,000 flight cycles. 

In addition, Boeing Alert Service 

Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010, specifies a 

compliance threshold for certain Model 

747–400, –400D, and –400F series 

airplanes (i.e., Groups 6 and 7 airplanes) 

of 12,000 total flight cycles or within 

1,500 flight cycles after the date of 

Boeing Alert Service Bulletin 747– 

53A2785, dated February 12, 2009, 

(whichever occurs later). The repetitive 

interval for those airplanes is 6,000 

flight cycles. 

In light of this revised service 

information, we have revised this 

supplemental NPRM to refer to Boeing 

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010. In 

addition, we have reformatted this 

supplemental NPRM to specify certain 

required actions by airplane group. 

We have also added paragraph (r) to 

this supplemental NPRM to give credit 

for accomplishing the inspections and 

repairs before the effective date of this 

AD, as specified in Boeing Alert Service 

Bulletin 747–53A2785, dated February 

12, 2009. 

Request To Refer to Service 

Information Instead of the Drawing 

Boeing requested that we revise 

paragraph (h) of the original NPRM 

(September 28, 2009 (74 FR 49351)) to 

refer to ‘‘the service bulletin repair 

drawing reference’’ instead of ‘‘drawing 

691U0145.’’ Boeing explained that they 

were in the process of revising Boeing 

Alert Service Bulletin 747–53A2785 to 

change Drawing 691U0145 into an 

orderable kit, which means that the 

repair drawing number will change. 

We agree with the commenter’s 

request to remove references to a 

particular drawing since the number 

will change. Based on Boeing’s 

comment, we have revised this 

supplemental NPRM to refer to Boeing 

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, for the 

outer chord repair. 

Requests To Add Acceptable Method of 

Compliance Information 

Boeing requested that paragraph (j) of 

the original NPRM (September 28, 2009 

(74 FR 49351)) (i.e., paragraph (o) of this 

supplemental NPRM) be revised to add 

that accomplishment of the inspections 

required by AD 2009–18–07, 

Amendment 39–16003 (74 FR 43629, 

August 27, 2009); or AD 2006–05–02, 

Amendment 39–14499 (71 FR 10605, 

March 2, 2006) (as superseded by AD 

2010–01–01, Amendment 39–16157 (75 

FR 1533, January 12, 2010)); as 

applicable; is acceptable for compliance 

with the inspection requirements of 

paragraphs (h) and (i) of the original 

NPRM. 

Boeing explained that Boeing Alert 

Service Bulletin 747–53A2785, dated 

February 12, 2009, states that when the 

inspections ‘‘per the fatigue test ADs 

2009–18–07, Amendment 39–16003 (74 

FR 43629, August 27, 2009) or 2006–05– 

02, Amendment 39–14499 (71 FR 

10605, March 2, 2006)’’ are 

accomplished, the inspections per the 

original NPRM (September 28, 2009 (74 

FR 49351)) and Boeing Alert Service 

Bulletin 747–53A2785, dated February 

12, 2009, are satisfied. Therefore, 

accomplishment of the inspections 

required by AD 2009–18–07 or 2006– 

05–02 (as superseded by AD 2010–01– 

01, Amendment 39–16157 (75 FR 1533, 

January 12, 2010)) is acceptable for 

compliance with the inspection 

requirements of paragraphs (g), (h), and 

(i) of the original NPRM. Boeing 

reasoned that the information should be 

included in paragraph (j) of the original 

NPRM. 

Boeing also requested that we revise 

paragraph (j) of the original NPRM 

(September 28, 2009 (74 FR 49351)) to 

replace the reference to AD 2005–20–30, 

Amendment 39–14327 (70 FR 59252, 

October 12, 2005), with a reference to 

AD 2009–18–07, Amendment 39–16003 

(74 FR 43629, August 27, 2009). Boeing 

explained that AD 2005–20–30 has been 

superseded by AD 2009–18–07. 

All Nippon Airways (ANA) also 

requested that paragraph (j) of the 

original NPRM (September 28, 2009 (74 

FR 49351)) be revised to refer to both 

paragraphs (g) and (h) of the original 

NPRM to clarify AMOC requirements. 

ANA explained that paragraph (j) of the 

original NPRM specifies that 

accomplishing the inspections required 

by AD 2005–20–30, Amendment 39– 

14327 (70 FR 59252, October 12, 2005) 

(which was superseded by AD 2009–18– 

07, Amendment 39–16003 (74 FR 

43629, August 27, 2009)); or AD 2006– 

05–02, Amendment 39–14499 (71 FR 

10605, March 2, 2006) (which was 

superseded by AD 2010–01–01, 

Amendment 39–16157 (75 FR 1533, 

January 12, 2010)); is an acceptable 

method of compliance for the 

inspections required by paragraph (g) of 

the original NPRM. ANA reasoned 

further, that paragraph (g) of the original 

NPRM refers only to the initial 

inspection, and paragraph (h) of the 

original NPRM refers to the repetitive 

inspection. 

We agree that accomplishing the 

detailed inspections required by AD 

2009–18–07, Amendment 39–16003 (74 


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FR 43629, August 27, 2009); or AD 

2010–01–01, Amendment 39–16157 (75 

FR 1533, January 12, 2010); as 

applicable; is acceptable for compliance 

with the detailed inspection 

requirements of paragraphs (g), (h), and 

(i) of this supplemental NPRM. 

Therefore, in paragraph (o) of this 

supplemental NPRM (which 

corresponds to paragraph (j) of the 

original NPRM (74 FR 49351, September 

28, 2009)), we have referred to 

paragraphs (g), (h), (l), and (m), since the 

actions specified by paragraph (o) of this 

supplemental NPRM are acceptable for 

compliance with those paragraphs. 

We also agree to revise paragraph (o) 

of this supplemental NPRM to reference 

to current AD 2009–18–07, Amendment 

39–16003 (74 FR 43629, August 27, 

2009); and AD 2010–01–01, 

Amendment 39–16157 (75 FR 1533, 

January 12, 2010). In addition, we have 

referenced the current ADs in paragraph 

(b) of this supplemental NPRM, since 

those ADs are affected by this 

supplemental NPRM. 

Request To Include Latest Revision of 

Service Information 

Boeing requested that we revise 

paragraph (j) of the original NPRM 

(September 28, 2009 (74 FR 49351)) (i.e., 

paragraph (o) of this supplemental 

NPRM), to refer to Boeing Alert Service 

Bulletin 747–53A2349, Revision 3, 

dated October 2, 2008, instead of 

Revision 2, dated April 3, 2003, of that 

service bulletin. 

We agree that this supplemental 

NPRM should refer to the latest service 

information. We have revised paragraph 

(o) of this supplemental NPRM to refer 

to Boeing Alert Service Bulletin 747– 

53A2349, Revision 3, dated October 2, 

2008. 

Request To Revise Boeing Delegated 

Option Authorization (DOA) to Boeing 

Organization Designation 

Authorization (ODA) 

Boeing requested that we revise any 

occurrence of the phrase ‘‘Boeing DOA’’ 

in the original NPRM (September 28, 

2009 (74 FR 49351)) to ‘‘Boeing ODA’’ 

in this supplemental NPRM. Boeing 

explained that Boeing Commercial 

Airplanes has changed from ‘‘DOA’’ to 

‘‘ODA.’’ 

We agree to revise ‘‘Boeing DOA’’ to 

‘‘Boeing ODA’’ in this supplemental 

NPRM. Boeing Commercial Airplanes 

has received an ODA, which replaces 

their previous designation as a DOA 

holder. We have revised paragraph (s) of 

this supplemental NPRM to delegate the 

authority to approve an AMOC for any 

repair required by this AD to the Boeing 

Commercial ODA. 

Clarification of ‘‘PART 3—REPAIR’’ 

The installation of a new outer chord 

repair specified in Section ‘‘PART 3— 

REPAIR’’ of Boeing Alert Service 

Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010, includes replacing 

any existing SRM outer chord repair 

with a new repair, repairing cracked 

outer chords, replacing cracked frame 

attach angles or clips, and contacting 

Boeing for repair instructions and doing 

the repair for main upper sill web 

cracks. 

Clarification of Service Bulletin 

The ‘‘detailed inspection of the upper 

main sill web and frame attachment 

angles (or clips) for crack(s)’’ in the 

second column, sixth row down, on 

page 26 of Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010, is not in the Accomplishment 

Instructions of that document. PART 

3—REPAIR of the Accomplishment 

Instructions in Boeing Alert Service 

Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010, is correct; there is 

no detailed inspection necessary as part 

of the repair. We note that a detailed 

inspection of the upper main sill 

(including the sill web and frame 

attachment angles (or clips) for cracks) 

is already required in PART 2— 

INSPECTION of the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. 

FAA’s Determination 

We are proposing this supplemental 

NPRM because we evaluated all 

pertinent information and determined 

an unsafe condition exists and is likely 

to exist or develop on other products of 

these same type designs. Certain 

changes described above expand the 

scope of the original NPRM (September 

28, 2009 (74 FR 49351)). As a result, we 

have determined that it is necessary to 

reopen the comment period to provide 

additional opportunity for the public to 

comment on this supplemental NPRM. 

Proposed Requirements of the 

Supplemental NPRM 

This supplemental NPRM would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed under ‘‘Differences Between 

the Supplemental NPRM and the 

Service Information.’’ 

Differences Between the Supplemental 

NPRM and the Service Information 

Boeing Alert Service Bulletin 747– 

53A2785, Revision 1, dated July 15, 

2010, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by an 

Authorized Representative for the 

Boeing Commercial Airplanes ODA 

whom we have authorized to make 

those findings. 

Explanation of Change to Costs of 

Compliance 

Since issuance of the original NPRM 

(September 28, 2009 (74 FR 49351)), we 

have increased the labor rate used in the 

Costs of Compliance from $80 per workhour to $85 per work-hour. The Costs of 

Compliance information, below, reflects 

this increase in the specified labor rate. 

Costs of Compliance 

We estimate that this proposed AD 

affects 165 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

Action Work hours Parts cost Cost per product 

Number of 

U.S.-registered 

airplanes 

Cost on U.S. operators 

Inspection (Groups 1, 3, 5–6) ........ 6 work-hours × 

$85 per hour = 

$510 

$0 $510 per inspection cycle.86 $43,860 per inspection cycle. 

Inspection (Groups 2, 4, 7) ............ 3 work-hours × 

$85 per hour = 

$255 

$0 $255 per inspection cycle.79 $20,145 per inspection cycle. 


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We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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 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 this 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. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2009–0794; Directorate Identifier 2009– 

NM–035–AD. 

(a) Comments Due Date 

We must receive comments by February 

13, 2012. 

(b) Affected ADs 

AD 2009–18–07, Amendment 39–16003 

(74 FR 43629, August 27, 2009); and AD 

2010–01–01, Amendment 39–16157 (75 FR 

1533, January 12, 2010); affect this AD. 

(c) Applicability 

This AD applies to all The Boeing 

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

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

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

747SR, and 747SP series airplanes; 

certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53: Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

in the main entry door number 1 upper main 

sill outer chord, along the bend radius of the 

chord on several airplanes. We are issuing 

this AD to detect and correct such cracks, 

which could result in loss of structural 

integrity of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection for Group 1 Through 4 

Airplanes 

For Group 1 through 4 airplanes as 

identified in Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010: At the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraphs (p) and (q) of this 

AD, do a one-time general visual inspection 

to identify any existing structural repair 

manual (SRM) repairs of the upper main sill 

outer chord of the left and right main entry 

door 1, as applicable. Remove any existing 

SRM outer chord repair that is found, before 

further flight, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. In addition, after doing 

the one-time general visual inspection to 

identify any existing SRM repairs of the 

upper main sill outer chord of the left and 

right main entry door 1, before further flight, 

do a detailed inspection for cracks of the 

main upper sill outer chord, web, and frame 

attachment angles (or clips) of the left and 

right main entry door 1, as applicable. Do all 

actions in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. If no crack and no 

existing SRM outer chord repair is found 

during any inspection required by this 

paragraph, at the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraphs (p) and (q) of this 

AD, repeat thereafter the detailed inspection 

for cracks, at intervals specified in paragraph 

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

Bulletin 747–53A2785, Revision 1, dated July 

15, 2010, until the outer chord repair 

specified in Part 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010, is installed. 

(h) Inspection for Group 5 Through 7 

Airplanes 

For Group 5 through 7 airplanes as 

identified in Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010: At the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraphs (p) and (q) of this 

AD, do a detailed inspection for cracks of the 

main upper sill outer chord, web, and frame 

attachment angles (or clips) of the left and 

right main entry door 1, as applicable, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. If no crack is found 

during any inspection required by this 

paragraph, at the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraph (p) and (q) of this AD, 

repeat thereafter the detailed inspection for 

cracks, at intervals specified in paragraph 

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

Bulletin 747–53A2785, Revision 1, dated July 

15, 2010, until the outer chord repair 

specified in Part 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010, is installed. 

(i) Repair for Group 1 Through 4 Airplanes 

For Group 1 through 4 airplanes as 

identified in Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010: If an existing SRM outer chord repair 

is found and removed during the inspection 

required by paragraph (g) of this AD, before 

further flight, install a new outer chord repair 

in accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. 

(j) Repair of Outer Chord Crack or Cracked 

Frame Attachment Angles (or Clips) 

If any outer chord crack or cracked frame 

attachment angles (or clips) is found during 

any inspection required by paragraph (g) or 

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


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accordance with Part 3 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. 

(k) Repair of Upper Main Sill Web Crack 

If any upper main sill web crack is found 

during any inspection required by paragraph 

(g) or (h) of this AD, before further flight, 

repair the crack using a method approved in 

accordance with the procedures specified in 

paragraph (s) of this AD. 

(l) Inspection 

If any upper main sill web or frame 

attachment angles (or clips) have been 

repaired as specified in PART 3—REPAIR of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, and the outer 

chord repair specified in PART 3—REPAIR of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, has not been 

installed, at the applicable time specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, except as 

provided by paragraphs (p) and (q) of this 

AD, do a detailed inspection for cracks as 

specified in paragraph (g) or (h) of this AD, 

as applicable, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010. Repeat the inspections 

in paragraph (g) or (h) of this AD, as 

applicable, thereafter at intervals specified in 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010. 

(m) Post-Repair Inspection 

For airplanes having the outer chord repair 

installed as specified in PART 3—REPAIR of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010: At the 

applicable time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2785, Revision 1, dated July 

15, 2010, except as provided by paragraphs 

(p) and (q) of this AD, do a detailed 

inspection for cracks of the left and right 

main entry door 1 upper sill, as applicable, 

with the outer chord repair installed, in 

accordance with PART 5—AFTER-REPAIR 

INSPECTION of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2785, Revision 1, dated July 15, 

2010. Repeat the inspection for cracks 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010. 

(n) Repair of Any Crack Found From PostRepair Inspection 

Repair any crack found during any 

inspection required by paragraph (m) of this 

AD, before further flight, using a method 

approved in accordance with the procedures 

specified in paragraph (s) of this AD. 

(o) Credit for Inspections Required by AD 

2009–18–07, Amendment 39–16003 (74 FR 

43629, August 27, 2009), or AD 2010–01–01, 

Amendment 39–16157 (75 FR 1533, January 

12, 2010) 

Accomplishing the main entry door 1 

cutout detailed inspection required by AD 

2009–18–07, Amendment 39–16003 (74 FR 

43629, August 27, 2009); or AD 2010–01–01, 

Amendment 39–16157 (75 FR 1533, January 

12, 2010); as applicable; before the effective 

date of this AD is acceptable for compliance 

with the detailed inspection requirements of 

paragraphs (g), (h), (l), and (m) of this AD 

only. The one-time general visual inspection 

of paragraph (g) of this AD is still required. 

Note 1: For all applicable airplanes that 

have accumulated 22,000 total flight cycles 

or more after October 1, 2009 (the effective 

date of AD 2009–18–07, Amendment 39– 

16003 (74 FR 43629, August 27, 2009)), AD 

2009–18–07 requires accomplishing the main 

entry door 1 cutout detailed inspection in 

accordance with Boeing Alert Service 

Bulletin 747–53A2349, Revision 3, dated 

October 2, 2008. For all applicable airplanes 

(except 747–400 series airplanes modified to 

the 747–400 large cargo freighter (LCF) 

configuration) that have accumulated 22,000 

total flight cycles or more after February 16, 

2010 (the effective date of AD 2010–01–01, 

Amendment 39–16157 (75 FR 1533, January 

12, 2010)), AD 2010–01–01 requires 

accomplishing the main entry door 1 cutout 

detailed inspection in accordance with 

Boeing Alert Service Bulletin 747–53A2500, 

Revision 1, dated September 25, 2008. For 

Model 747–400 series airplanes modified to 

the Model 747–400 LCF configuration and 

having accumulated 15,000 total flight cycles 

or more as of February 16, 2010, AD 2010– 

01–01 requires accomplishing the 

inspections in accordance with Boeing Alert 

Service Bulletin 747–53A2500, Revision 1, 

dated September 25, 2008. 

(p) Exception to the Service Information 

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

Boeing Alert Service Bulletin 747–53A2785, 

Revision 1, dated July 15, 2010, specifies a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ or ‘‘after the date on 

Revision 1 of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(q) Exception to Compliance Time 

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

Service Bulletin 747–53A2785, Revision 1, 

dated July 15, 2010, specifies a compliance 

time of ‘‘within’’ a specified ‘‘total flightcycles,’’ this AD requires compliance ‘‘before 

the accumulation’’ of the specified total flight 

cycles. 

(r) Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

Doing the inspections and repairs, in 

accordance with Boeing Alert Service 

Bulletin 747–53A2785, dated February 12, 

2009, before the effective date of this AD, is 

acceptable for compliance with the 

corresponding inspections and repairs 

required by paragraphs (g), (h), (i), (j), (k), (l), 

(m), and (n) of this AD. 

(s) 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 

(t) Related Information 

(1) For more information about this AD, 

contact Ivan Li, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 917–6437; fax (425) 

917–6590; email: ivan.li@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; email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

(425) 227–1221. 

Issued in Renton, Washington, on 

December 22, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–33376 Filed 12–28–11; 8:45 am] 

BILLING CODE 4910–13–P 


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