Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36139 

21019 Somma Lombardo (VA) Italy, ATTN: 

Giovanni Cecchelli; telephone 39–0331– 

711133; fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

(5) You may review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137 or at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call (202) 741–6030, or go 

to: http://www.archives.gov/federal_register/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Fort Worth, Texas, on May 30, 

2012. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–14385 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1255; Directorate 

Identifier 2010–NM–182–AD; Amendment 

39–17084; AD 2012–12–05] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding two 

existing airworthiness directives (ADs) 

for certain Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

The first existing AD currently requires, 

for certain airplanes, repetitive 

inspections of the Station (STA) 348.2 

frame to detect cracking under the stop 

fittings and intercostal flanges at 

stringers S–14L, S–15L, and S–16L, and 

corrective action if necessary. The 

second existing AD currently requires 

repetitive inspections to detect cracking 

of the intercostal webs, attachment 

clips, and stringer splice channels, and 

corrective action if necessary. This new 

AD requires that the inspection for 

cracking under the stop fittings be done 

on additional airplanes; extends the 

repetitive interval for certain airplanes; 

adds a one-time inspection to detect 

missing fasteners; and updates or adds 

certain inspection and repair 

instructions. This new AD also requires, 

for certain airplanes, repetitive 

inspections of the cargo barrier net 

fitting for cracking, and repair if 

necessary. This new AD also adds, for 

certain airplanes, repetitive inspections 

for cracking of the stringer S–15L aft 

intercostal, and repair if necessary. This 

AD was prompted by reports of cracking 

of the STA 348.2 frame above the two 

outboard fasteners attaching the frame 

inner chord and door stop fittings, and 

in the outboard chord at stringer S–16L. 

We have also received reports of 

missing fasteners in the STA 348.2 

frame inner chord. We are issuing this 

AD to detect and correct fatigue 

cracking of the intercostals on the 

forward and aft sides of the forward 

entry door cutout, which could result in 

loss of the forward entry door and rapid 

decompression of the airplane. 

DATES: This AD is effective July 23, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of July 23, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 9, 2009 (74 FR 38901, 

August 5, 2009). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 1, 2005 (70 FR 56361, 

September 27, 2005). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of June 4, 2004 (69 FR 23646, April 

30, 2004). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility between 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6450; fax: (425) 917–6590; email: 

Alan.Pohl@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede airworthiness 

directives AD 2004–09–09, Amendment 

39–13598 (69 FR 23646, April 30, 2004); 

and AD 2009–16–14, Amendment 39– 

15987 (74 FR 38901, August 5, 2009). 

Those ADs apply to the specified 

products. The NPRM published in the 

Federal Register on November 28, 2011 

(76 FR 72858). The NPRM proposed to 

retain certain requirements of AD 2004– 

09–09 and AD 2009–16–14. The NPRM 

proposed to also add airplanes to the 

applicability for the high frequency 

eddy current (HFEC) inspection for 

cracking of the stop fittings at the shear 

web at the STA 348.2 frame; extend the 

repetitive interval for the HFEC 

inspection of the STA 348.2 frame for 

Model 737–200C airplanes; add an 

inspection to detect missing fasteners of 

the STA 348.2 frame inner chord; and 

update or add certain inspection and 

repair instructions. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (76 FR 72858, 

November 28, 2011) and the FAA’s 

response to each comment. 

Support for NPRM (76 FR 72858, 

November 28, 2011) 

Boeing concurs with the contents of 

the NPRM (76 FR 72858, November 28, 

2011). 

Requests To Remove or Revise 

Exception to Certain Service 

Information 

Southwest Airlines (SWA) asked that 

paragraph (r) of the NPRM (76 FR 

72858, November 28, 2011) be removed, 

or revised to provide clarification. SWA 

stated that the exception specified in 

paragraph (r) of the NPRM does not 

allow the sequence of steps in the Work 

Instructions of Boeing Alert Service 

Bulletin 737–53A1240, Revision 1, 

dated June 29, 2010, to be changed. 

SWA added that it has serious concerns 


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36140 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 

that this paragraph effectively 

eliminates all flexibility when 

accomplishing open access, the order of 

which locations get inspected, and close 

access. SWA noted that this becomes 

very difficult in a maintenance 

environment where other activities may 

be worked concurrently. SWA asked if 

the intent of the exception in paragraph 

(r) of the NPRM is to make removing the 

windscreen before the lavatory and 

removing the fasteners identified in 

Circle Note 1 prior to removing the 

fasteners identified in Circle Note 2 

conditions of compliance. SWA 

understands that certain steps contained 

in Boeing Alert Service Bulletin 737– 

53A1240, Revision 1, dated June 29, 

2010, might have to be accomplished in 

a specific order. However, SWA noted 

that the umbrella restriction imposed by 

paragraph (r) of the NPRM goes beyond 

that intent and results in restrictions 

when performing maintenance. 

Scandanavian Airlines Systems (SAS) 

asked that we include an option of 

removing the shear web before 

accomplishing the inspection specified 

in Boeing Alert Service Bulletin 737– 

53A1204, Revision 2, dated June 24, 

2010, as part of the access procedures 

specified in the NPRM (76 FR 72858, 

November 28, 2011). SAS stated that it 

has previously accomplished the 

inspections as an alternative method of 

compliance (AMOC) to AD 2009–16–14, 

Amendment 39–15987 (74 FR 38901, 

August 5, 2009). SAS noted that it also 

received clarification from the 

manufacturer regarding the shear web 

removal step in Parts 1 and 2 of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–53A1204, 

Revision 2, dated June 24, 2010. SAS 

stated that the shear web removal is not 

part of the inspection procedures 

specified in Boeing Alert Service 

Bulletin 737–53A1204, Revision 1, 

dated March 26, 2007. 

We agree with the commenters for the 

reasons provided. We have revised 

paragraph (r) of this AD accordingly. 

Request To Include Reference to 

Previously Approved AMOCs 

SWA asked that we include a 

reference to AMOCs approved for AD 

2005–20–03, Amendment 39–14296 (70 

FR 56361, September 27, 2005) in the 

NPRM (76 FR 72858, November 28, 

2011). SWA pointed out that paragraph 

(m)(4) of AD 2009–16–14, Amendment 

39–15987 (74 FR 38901, August 5, 

2009), stated that ‘‘AMOCs approved 

previously in accordance with AD 

2005–20–03 are approved as AMOCs for 

the corresponding provisions of this AD, 

provided the repetitive inspection 

intervals (if any) do not exceed 6,000 

flight cycles.’’ SWA specified that 

paragraph (t)(5) of the NPRM can be 

interpreted to mean that an AMOC 

issued for AD 2005–20–03, which was 

approved as an AMOC to AD 2009–16– 

14, will be considered as an AMOC to 

the NPRM. 

We agree with the commenter that 

AMOCs approved for AD 2005–20–03, 

Amendment 39–14296 (70 FR 56361, 

September 27, 2005), as specified in 

paragraph (m)(4) of AD 2009–16–14, 

Amendment 39–15987 (74 FR 38901, 

August 5, 2009), are still approved for 

the corresponding requirements of this 

AD. For clarity, we have added a new 

paragraph (t)(5) to this AD to include 

that information, and we reidentified 

the existing paragraph (t)(5) of the 

NPRM (76 FR 72858, November 28, 

2011) as paragraph (t)(6) in this final 

rule. 

Explanation of Additional Changes 

Made to This AD 

We have clarified the compliance 

time in paragraph (q) of this AD by 

adding the phrase ‘‘whichever occurs 

later.’’ 

We have updated certain headings 

throughout this AD. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

72858, November 28, 2011) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 72858, 

November 28, 2011). 

Costs of Compliance 

We estimate that this AD affects 581 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

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

Inspections for cracking under the 

stop fittings and intercostal flanges 

[retained from AD 2004–09–09, 

Amendment 39–13598 (69 FR 

23646, April 30, 2004)].

18 work-hours × $85 per hour = 

$1,530 per inspection cycle.

$0 $1,530 per inspection cycle.$888,930 per inspection 

cycle. 

Inspection of areas forward of the aft 

entry door [retained from AD 2009– 

16–14, Amendment 39–15987 (74 

FR 38901, August 5, 2009)].

2 work-hours × $85 per hour = $170 

per inspection cycle.

0 $170 per inspection cycle.$98,770 per inspection 

cycle. 

Inspection of areas aft of the forward 

entry door [retained from AD 2009– 

16–14, Amendment 39–15987 (74 

FR 38901, August 5, 2009)].

1 work-hour × $85 per hour = $85 per 

inspection cycle.

0 $85 per inspection 

cycle.

$49,385 per inspection 

cycle. 

Inspection for missing fasteners [new 

action].

1 work-hour × $85 per hour = $85 ..... 476 $561 ..................... $325,941. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspections. We have no way of 

determining the number of aircraft that 

might need these repairs: 


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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36141 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Repair of cracking if done in accordance with a method approved by the FAA.Unknown ................................... Unknown ................................... Unknown. 

Repair of cracking if done in accordance with Boeing Alert Service Bulletin 737–53A1240, Revision 1, dated June 29, 2010.24 work-hours ........................... $11,856 ..................................... $13,896. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2004–09–09, Amendment 39–13598 (69 

FR 23646, April 30, 2004); and AD 

2009–16–14, Amendment 39–15987 (74 

FR 38901, August 5, 2009); and adding 

the following new AD: 

2012–12–05 The Boeing Company: 

Amendment 39–17084; Docket No. 

FAA–2011–1255; Directorate Identifier 

2010–NM–182–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective July 23, 2012. 

(b) Affected ADs 

This AD supersedes AD 2004–09–09, 

Amendment 39–13598 (69 FR 23646, April 

30, 2004); and AD 2009–16–14, Amendment 

39–15987 (74 FR 38901, August 5, 2009). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes, 

certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking of the station (STA) 348.2 frame 

above the two outboard fasteners attaching 

the frame inner chord and door stop fittings, 

and in the outboard chord at stringer S–16L. 

We have also received reports of missing 

fasteners in the STA 348.2 frame inner chord. 

We are issuing this AD to detect and correct 

fatigue cracking of the intercostals on the 

forward and aft sides of the forward entry 

door cutout, which could result in loss of the 

forward entry door and rapid decompression 

of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Initial and Repetitive 

Inspections at STA 348.2 for Model 737– 

200C Series Airplanes 

This paragraph restates the requirements of 

paragraph (a) of AD 2004–09–09, 

Amendment 39–13598 (69 FR 23646, April 

30, 2004), with revised service information. 

For Model 737–200C series airplanes: Except 

as provided by paragraph (h) of this AD, prior 

to the accumulation of 46,000 total flight 

cycles, or within 2,250 flight cycles after June 

4, 2004 (the effective date of AD 2004–09– 

09), whichever occurs later, do detailed and 

eddy current inspections of the STA 348.2 

frame for cracking under the stop fittings and 

intercostal flanges at stringers 14L, 15L, and 

16L by accomplishing paragraphs 3.A and 

3.B.1 through 3.B.7 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1240, dated April 10, 2003; or by 

accomplishing Part 1 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1240, Revision 1, dated June 29, 

2010. Do the actions in accordance with 

Boeing Alert Service Bulletin 737–53A1240, 

dated April 10, 2003; or Boeing Alert Service 

Bulletin 737–53A1240, Revision 1, dated 

June 29, 2010. Any applicable repair must be 

accomplished prior to further flight. Repeat 

the inspections thereafter at intervals not to 

exceed 6,000 flight cycles. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 737–53A1240, Revision 1, dated 

June 29, 2010, may be used to accomplish the 

actions required by this paragraph. 

(h) Retained Corrective Action for Paragraph 

(g) of This AD 

This paragraph restates the requirements of 

paragraph (b) of AD 2004–09–09, 

Amendment 39–13598 (69 FR 23646, April 

30, 2004), with revised service information. 

If any crack is found during any inspection 

required by paragraph (g) of this AD, and 

Boeing Alert Service Bulletin 737–53A1240, 

dated April 10, 2003; or Boeing Alert Service 

Bulletin 737–53A1240, Revision 1, dated 

June 29, 2010; specifies to contact Boeing for 

appropriate action: Before further flight, 

repair in accordance with a method approved 

by the Manager, Seattle Aircraft Certification 

Office (ACO), FAA; or using a method 

approved in accordance with the procedures 

specified in paragraph (t) of this AD. 


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36142 Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 

(i) Retained Initial Compliance Time for 

Model 737–100, –200, –200C, –300, –400, and 

–500 Series Airplanes 

This paragraph restates the requirements of 

paragraph (f) of AD 2009–16–14, Amendment 

39–15987 (74 FR 38901, August 5, 2009). For 

all Model 737–100, –200, –200C, –300, –400, 

and –500 series airplanes, as identified in 

Boeing Alert Service Bulletin 737–53A1204, 

Revision 1, dated March 26, 2007: Before the 

accumulation of 15,000 total flight cycles, or 

within 4,500 flight cycles after November 1, 

2005 (the effective date of AD 2005–20–03, 

Amendment 39–14296 (70 FR 56361, 

September 27, 2005)), whichever occurs later: 

Do the inspections required by paragraphs (k) 

and (l) of this AD. 

(j) Retained Initial Compliance Time for 

Model 737–200C Series Airplanes 

This paragraph restates the requirements of 

paragraph (g) of AD 2009–16–14, 

Amendment 39–15987 (74 FR 38901, August 

5, 2009). For all Model 737–200C series 

airplanes, as identified in Boeing Alert 

Service Bulletin 737–53A1204, Revision 1, 

dated March 26, 2007: Before the 

accumulation of 15,000 total flight cycles, or 

within 4,500 flight cycles after September 9, 

2009 (the effective date of AD 2009–16–14), 

whichever occurs later, do the inspection 

required by paragraph (m) of this AD. 

(k) Retained Initial Inspection for Group 1 

Configuration Airplanes 

This paragraph restates the requirements of 

paragraph (h) of AD 2009–16–14, 

Amendment 39–15987 (74 FR 38901, August 

5, 2009), with revised service information. 

For Group 1 airplanes identified in Boeing 

Alert Service Bulletin 737–53A1204, 

Revision 1, dated March 26, 2007: Perform a 

detailed inspection for cracking of the 

intercostal web, attachment clips, and 

stringer splice channels; and a high 

frequency eddy current (HFEC) inspection for 

cracking of the stringer splice channels 

located forward and aft of the forward entry 

door; and do all applicable corrective actions 

before further flight; in accordance with Parts 

1 and 2 of the Work Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1204, dated June 19, 2003, or Boeing Alert 

Service Bulletin 737–53A1204, Revision 1, 

dated March 26, 2007; or in accordance with 

Parts 1, 2, 4, and 5 of the Work Instructions 

of Boeing Alert Service Bulletin 737– 

53A1204, Revision 2, dated June 24, 2010. 

After September 9, 2009 (the effective date of 

AD 2009–16–14, Amendment 39–15987 (74 

FR 38901, August 5, 2009), and until the 

effective date of this AD, Boeing Alert 

Service Bulletin 737–53A1204, Revision 1, 

dated March 26, 2007; or Boeing Alert 

Service Bulletin 737–53A1204, Revision 2, 

dated June 24, 2010; may be used to 

accomplish the actions required by this 

paragraph. As of the effective date of this AD, 

only Boeing Alert Service Bulletin 737– 

53A1204, Revision 2, dated June 24, 2010, 

may be used to accomplish the actions 

required by this paragraph. 

(l) Retained Initial Inspection for Cargo 

Configuration Airplanes (Forward of the 

Forward Entry Door) 

This paragraph restates the requirements of 

paragraph (i) of AD 2009–16–14, Amendment 

39–15987 (74 FR 38901, August 5, 2009), 

with revised service information. For Group 

2 cargo airplanes identified in Boeing Alert 

Service Bulletin 737–53A1204, Revision 1, 

dated March 26, 2007: Perform a detailed 

inspection for cracking of the intercostal 

webs and attachment clips located forward of 

the forward entry door, and do all applicable 

corrective actions before further flight, in 

accordance with Part 3 of the Work 

Instructions of Boeing Special Attention 

Service Bulletin 737–53–1204, dated June 19, 

2003, or Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007; 

or in accordance with Part 3 of Boeing Alert 

Service Bulletin 737–53A1204, Revision 2, 

dated June 24, 2010. After September 9, 2009 

(the effective date of AD 2009–16–14, 

Amendment 39–15987 (74 FR 38901, August 

5, 2009), and until the effective date of this 

AD, Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007; 

or Boeing Alert Service Bulletin 737– 

53A1204, Revision 2, dated June 24, 2010; 

may be used to accomplish the actions 

required by this paragraph. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 737–53A1204, Revision 2, dated 

June 24, 2010, may be used to accomplish the 

actions required by this paragraph. 

(m) Retained Initial Inspection for Cargo 

Configuration Airplanes (Aft of the Forward 

Entry Door) 

This paragraph restates the requirements of 

paragraph (j) of AD 2009–16–14, Amendment 

39–15987 (74 FR 38901, August 5, 2009), 

with revised service information. For Group 

2 cargo airplanes identified in Boeing Alert 

Service Bulletin 737–53A1204, Revision 1, 

dated March 26, 2007: Perform a detailed 

inspection for cracking of the intercostal 

webs and attachment clips located aft of the 

forward entry door, and do all applicable 

corrective actions before further flight, in 

accordance with Part 4 of the Work 

Instructions of Boeing Alert Service Bulletin 

737–53A1204, Revision 1, dated March 26, 

2007; or in accordance with Part 3 of Boeing 

Alert Service Bulletin 737–53A1204, 

Revision 2, dated June 24, 2010. As of the 

effective date of this AD, only Boeing Alert 

Service Bulletin 737–53A1204, Revision 2, 

dated June 24, 2010, may be used to 

accomplish the actions required by this 

paragraph. 

(n) Retained Repeat Inspections 

This paragraph restates the requirements of 

paragraph (k) of AD 2009–16–14, 

Amendment 39–15987 (74 FR 38901, August 

5, 2009). Repeat the inspections required by 

paragraphs (k), (l), and (m) of this AD 

thereafter at intervals not to exceed 6,000 

flight cycles after the previous inspection, or 

within 3,000 flight cycles after September 9, 

2009 (the effective date of AD 2009–1614), 

whichever occurs later. 

(o) Retained Exceptions to Boeing Special 

Attention Service Bulletin 737–53–1204 

This paragraph restates the requirements of 

paragraph (l) of AD 2009–16–14, Amendment 

39–15987 (74 FR 38901, August 5, 2009), 

with revised service information. Do the 

actions required by paragraphs (i), (j), (k), (l), 

(m), and (n) of this AD by accomplishing all 

the applicable actions specified in the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1204, dated June 19, 2003; Boeing Alert 

Service Bulletin 737–53A1204, Revision 1, 

dated March 26, 2007; or Boeing Alert 

Service Bulletin 737–53A1204, Revision 2, 

dated June 24, 2010; except as provided by 

paragraphs (o)(1) and (o)(2) of this AD. After 

September 9, 2009 (the effective date of AD 

2009–16–14), and until the effective date of 

this AD, Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007; 

or Boeing Alert Service Bulletin 737– 

53A1204, Revision 2, dated June 24, 2010; 

may be used to accomplish the actions 

required by this paragraph. As of the effective 

date of this AD, only Boeing Alert Service 

Bulletin 737–53A1204, Revision 2, dated 

June 24, 2010, may be used to accomplish the 

actions required by this paragraph. 

(1) Where Boeing Special Attention Service 

Bulletin 737–53–1204, dated June 19, 2003; 

Boeing Alert Service Bulletin 737–53A1204, 

Revision 1, dated March 26, 2007; or Boeing 

Alert Service Bulletin 737–53A1204, 

Revision 2, dated June 24, 2010; specifies to 

contact Boeing for repair instructions: Before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (t) of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 737–53–1204, dated June 19, 2003; 

or Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007; 

specifies a compliance time relative to the 

date of a service bulletin, this AD requires 

compliance relative to September 9, 2009 

(the effective date of AD 2009–16–14, 

Amendment 39–15987 (74 FR 38901, August 

5, 2009). Where Boeing Special Attention 

Service Bulletin 737–53–1204, dated June 19, 

2003; or Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007; 

specifies a compliance time relative to the 

date of the initial release of a service bulletin, 

this AD requires compliance relative to 

November 1, 2005 (the effective date of AD 

2005–20–03, Amendment 39–14296 (70 FR 

56361, September 27, 2005)). 

(p) New One-Time Inspection for Missing 

Fasteners at STA 348.2 

For Groups 2 and 3 airplanes identified in 

Boeing Alert Service Bulletin 737–53A1240, 

Revision 1, dated June 29, 2010: Within 4,500 

flight cycles after the effective date of this 

AD, do a detailed inspection to detect 

missing fasteners of the STA 348.2 frame, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1240, Revision 1, dated June 29, 

2010, except as required by paragraph (r) of 

this AD. If any fastener is missing, before 

further flight, repair using a method 

approved in accordance with the procedures 

specified in paragraph (t) of this AD. 


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Federal Register / Vol. 77, No. 117 / Monday, June 18, 2012 / Rules and Regulations 36143 

(q) New Initial and Repetitive Inspections at 

STA 348.2 for Model 737–100, –200, –300, 

–400, and –500 Series Airplanes 

For Groups 2 and 3 airplanes identified in 

Boeing Alert Service Bulletin 737–53A1240, 

Revision 1, dated June 29, 2010: Before the 

accumulation of 15,000 total flight cycles, or 

within 4,500 flight cycles after the effective 

date of this AD, whichever occurs later, do 

HFEC and surface eddy current inspections 

for cracking of the frame, HFEC inspections 

for cracking of the reinforcement angle and 

shear web, and a detailed inspection for 

cracking of the STA 348.2 frame outer chord, 

inner chord, and reinforcement angle, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1240, Revision 1, dated June 29, 

2010, except as required by paragraph (r) of 

this AD. If any crack is found during any 

inspection required by this paragraph, before 

further flight, do all applicable corrective 

actions in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1240, Revision 1, 

dated June 29, 2010, except as required by 

paragraph (r) of this AD, and except where 

that service bulletin specifies to contact 

Boeing, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (t) of this 

AD. Repeat the inspections thereafter at 

intervals not to exceed 6,000 flight cycles. 

(r) New Exceptions to Boeing Alert Service 

Bulletins 737–53A1204 and 737–53A1240 

(1) Note 1 of paragraph 3.A of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1240, Revision 1, 

dated June 29, 2010, is to be disregarded 

when accomplishing the actions required by 

this AD. 

(2) The access and restoration instructions 

identified in the Work Instructions of Boeing 

Alert Service Bulletin 737–53A1204, 

Revision 2, dated June 24, 2010; and Boeing 

Alert Service Bulletin 737–53A1240, 

Revision 1, dated June 29, 2010; are not 

required by this AD. Operators may perform 

those actions in accordance with approved 

maintenance procedures. 

(3) The use of Boeing Drawing 65–88700 is 

not allowed when accomplishing the actions 

required by this AD in accordance with the 

Work Instructions of Boeing Alert Service 

Bulletin 737–53A1204, Revision 2, dated 

June 24, 2010; and Boeing Alert Service 

Bulletin 737–53A1240, Revision 1, dated 

June 29, 2010. 

(s) New Initial and Repetitive Inspections of 

the S–15L Aft Intercostal and Cargo Barrier 

Net Fitting for Model 737–200C Series 

Airplanes 

For Group 2 airplanes identified in Boeing 

Alert Service Bulletin 737–53A1204, 

Revision 2, dated June 24, 2010: Before the 

accumulation of 15,000 total flight cycles, or 

within 4,500 flight cycles after the effective 

date of this AD, whichever occurs later, do 

initial detailed and HFEC inspections for 

cracking of the S–15L aft intercostal between 

BS 348.2 and BS 360, and do a detailed 

inspection of the cargo barrier net fitting at 

the intercostal, in accordance with Figure 3 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1204, 

Revision 2, dated June 24, 2010. If any 

cracking is found, before further flight repair 

using a method approved in accordance with 

the procedures specified in paragraph (t) of 

this AD. Repeat the inspections thereafter at 

intervals not to exceed 6,000 flight cycles. 

(t) Alternative Methods of Compliance 

(AMOCs) 

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

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, it may be emailed 

to: 9-ANM-Seattle-ACO-AMOCRequests@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 approved previously in 

accordance with AD 2004–09–09, 

Amendment 39–13598 (69 FR 23646, April 

30, 2004), are approved as AMOCs for the 

corresponding requirements of this AD. 

(5) AMOCs approved previously in 

accordance with AD 2005–20–03, 

Amendment 39–14296 (70 FR 56361, 

September 27, 2005), are approved as 

AMOCs for the corresponding requirements 

of this AD, provided the repetitive inspection 

intervals (if any) do not exceed 6,000 flight 

cycles. 

(6) AMOCs approved previously in 

accordance with AD 2009–16–14, 

Amendment 39–15987 (74 FR 38901, August 

5, 2009), are approved as AMOCs for the 

corresponding requirements of this AD. 

(u) Related Information 

For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone (425) 917– 

6450; fax (425) 917–6590; email: 

Alan.Pohl@faa.gov. 

(v) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

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

51. 

(2) You must use the following service 

information to do the actions required by this 

AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 23, 2012. 

(i) Boeing Alert Service Bulletin 737– 

53A1240, Revision 1, dated June 29, 2010. 

(ii) Boeing Alert Service Bulletin 737– 

53A1204, Revision 2, dated June 24, 2010. 

(4) The following service information was 

approved for IBR on September 9, 2009 (74 

FR 38901, August 5, 2009). 

(i) Boeing Alert Service Bulletin 737– 

53A1204, Revision 1, dated March 26, 2007. 

(5) The following service information was 

approved for IBR on November 1, 2005 (70 

FR 56361, September 27, 2005). 

(i) Boeing Special Attention Service 

Bulletin 737–53–1204, dated June 19, 2003. 

(6) The following service information was 

approved for IBR on June 4, 2004 (69 FR 

23646, April 30, 2004). 

(i) Boeing Alert Service Bulletin 737– 

53A1240, dated April 10, 2003. 

(7) 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. 

(8) 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. 

(9) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr_locations.html. 

Issued in Renton, Washington, on June 4, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–14373 Filed 6–15–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1415; Directorate 

Identifier 2011–NM–145–AD; Amendment 

39–17089; AD 2012–12–09] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 717–200 

airplanes. This AD was prompted by 

reports of cracks found on the center 

section ribs of the horizontal stabilizers. 

This AD requires repetitive inspections 

for cracking of the aft face of the left and 

right rib hinge bearing lugs of the center 


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