Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47549 

of the effective date of this AD, Gulfstream 

Service Bulletin 100–31–284, Revision 1, 

dated May 27, 2011, must be used to 

accomplish the actions required by this 

paragraph. 

(4) Within 250 flight hours after June 25, 

2010 (the effective date of AD 2010–11–02, 

Amendment 39–16307 (75 FR 28485, May 21, 

2010)), but no later than within 6 months 

after the effective date of this AD: Verify that 

the log of modification of the relevant AFM 

includes a reference to MOD G1–20052, and, 

if no reference is found, revise the log of 

modification of the AFM to include a 

reference to the modification. 

(5) Doing the modifications specified in 

paragraphs (h)(1), (h)(2), (h)(3), and (h)(4) of 

this AD terminates the requirements of 

paragraph (g) of this AD. After the 

modifications have been done, the AFM 

limitation required by paragraph (g) of this 

AD may be removed from the AFM. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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: 

Tom Stafford, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1622; 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. 

(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. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on September 10, 2013. 

(i) Gulfstream Service Bulletin 100–31– 

284, Revision 1, dated May 27, 2011. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on June 25, 2010 (75 FR 

28485, May 21, 2010). 

(i) Gulfstream Service Bulletin 100–31– 

284, dated August 17, 2006. 

(ii) Honeywell Service Bulletin 80–0548– 

31–0001, dated April 1, 2006. 

(iii) Honeywell Service Bulletin 80–0548– 

31–0002, dated March 1, 2006. 

(iv) Honeywell Service Bulletin 80–5090– 

31–0001, dated March 1, 2006. 

(5) For service information identified in 

this AD, contact Gulfstream Aerospace 

Corporation, P.O. Box 2206, Mail Station D– 

25, Savannah, Georgia 31402–2206; 

telephone 800–810–4853; fax 912–965–3520; 

email pubs@gulfstream.com; Internet http:// 

www.gulfstream.com/product_support/ 

technical_pubs/pubs/index.htm. 

(6) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on July 9, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18768 Filed 8–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–1156; Directorate 

Identifier 2011–NM–205–AD; Amendment 

39–17500; AD 2013–13–12] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

airworthiness directive (AD) 2000–06– 

13 R1, which applied to certain The 

Boeing Company Model 737–200, 

–200C, –300, and –400 series airplanes. 

AD 2000–06–13 R1 required repetitively 

inspecting for cracking of the corners of 

the door frame and the cross beams of 

the aft cargo door, and corrective actions 

if necessary. AD 2000–06–13 R1 also 

required modifying the aft cargo door, 

which terminates the repetitive 

inspections. This new AD adds 

airplanes to the applicability, adds 

inspections and related investigative 

and corrective actions, revises certain 

inspection types, and reduces a certain 

compliance time for modifying the 

doors. This AD was prompted by reports 

of cracking in the forward and aft corner 

frames of the aft cargo door and in the 

lower cross beam. We are issuing this 

AD to prevent fatigue cracking of the 

corners of the door frame and the cross 

beams of the aft cargo door, which could 

result in rapid depressurization of the 

airplane. 

DATES: This AD is effective September 

10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 10, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of May 9, 2000 (65 FR 17583, 

April 4, 2000). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of December 24, 1998 (63 FR 

67769, December 9, 1998). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, Washington 98057–3356. 

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, 


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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 AD 2000–06–13 R1, 

Amendment 39–12317 (66 FR 36146, 

July 11, 2001), which revised AD 2000– 

06–13, Amendment 39–11654 (65 FR 

17583, April 4, 2000). AD 2000–06–13 

superseded AD 98–25–06, Amendment 

39–10931 (63 FR 67769, December 9, 

1998). AD 2000–06–13 R1 applied to the 

specified products. The NPRM 

published in the Federal Register on 

December 4, 2012 (77 FR 71723). The 

NPRM proposed to continue to require 

repetitively inspecting for cracking of 

the corners of the door frame and the 

cross beams of the aft cargo door; doing 

corrective actions if necessary; and 

modifying the aft cargo door, which 

terminates the repetitive inspections. 

The NPRM also proposed to add 

airplanes to the applicability, add 

inspections and related investigative 

and corrective actions, revise certain 

inspection types, and reduce a certain 

compliance time for modifying the 

doors. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 71723, 

December 4, 2012) and the FAA’s 

response to each comment. 

Request To Revise Compliance Time 

Boeing requested that we revise 

paragraph (o) of the NPRM (77 FR 

71723, December 4, 2012), which 

specified the compliance time by 

referring to paragraph 1.E. of Boeing 

Alert Service Bulletin 737–52A1153, 

dated July 13, 2011. Boeing requested 

that we change this compliance time to 

‘‘4,500 door flight cycles after the 

effective date of this AD’’ to avoid a 

potential conflict with other compliance 

times in the NPRM. Boeing explained a 

scenario in which an operator could 

comply with paragraph (o) of the NPRM 

within the required compliance time, 

but then be immediately out of 

compliance with the proposed 

inspection in paragraphs (p) and (q) of 

the NPRM. 

We partially agree with the request. 

As written, the compliance time in 

paragraph (o) of the NPRM (77 FR 

71723, December 4, 2012) could result 

in a compliance conflict with other 

requirements of this AD for doors 

subject to Boeing Alert Service Bulletin 

737–52A1079, Revision 7, dated 

December 17, 2010. We disagree, 

however, with Boeing’s requested 

compliance time, which would be 

unnecessarily more restrictive on 

operators. Also, the referenced doors 

that have accumulated fewer than 

27,000 total flight cycles should be 

provided the same compliance time as 

doors subject to Boeing Alert Service 

Bulletin 737–52A1153, dated July 13, 

2011. We have therefore revised 

paragraphs (p) and (q) in this final rule 

to change the compliance time to a 

threshold of 27,000 total flight cycles on 

the door, with a grace period of 4,500 

flight cycles. Since paragraph (u)(4) of 

the NPRM is therefore no longer 

necessary, we have removed that 

paragraph from this final rule. 

Request To Revise Requirement To 

Determine Door Configuration 

Southwest Airlines (SWA) requested 

that we revise paragraph (o) of the 

NPRM (77 FR 71723, December 4, 2012), 

which specified to ‘‘Inspect the door to 

determine the configuration, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin 737–52A1153, dated July 13, 

2011.’’ SWA considered that the intent 

of this proposed requirement could be 

accomplished by records research 

instead of a physical inspection. The 

commenter noted that the 

Accomplishment Instructions of this 

service bulletin specify only identifying 

the part number of the aft cargo door 

assembly, and does not specify a 

method of accomplishment. 

We agree with the commenter that a 

records review is acceptable in lieu of 

accomplishing an inspection to 

determine the configuration of the door. 

We have changed paragraph (o) 

accordingly in this final rule. 

Request To Refer To Revised Service 

Information 

All Nippon Airways (ANA) and 

Boeing requested that we revise the 

NPRM (77 FR 71723, December 4, 2012) 

to also refer to Boeing Special Attention 

Service Bulletin 737–52–1154, Revision 

1, dated August 3, 2011, in all locations 

where Boeing Service Bulletin 737–52– 

1154, dated December 17, 2010, is cited. 

The commenters noted that some 

locations of the NPRM referred to only 

the original version, but other 

paragraphs referred to the original 

version ‘‘as revised by Boeing Special 

Attention Service Bulletin 737–52– 

1154, Revision 1, dated August 3, 

2011.’’ 

We agree with the commenter and 

have revised paragraphs (r)(2) and (u)(2) 

in this final rule to also add ‘‘as revised 

by Boeing Special Attention Service 

Bulletin 737–52–1154, Revision 1, dated 

August 3, 2011,’’ after the original 

service bulletin citation. 

Request To Clarify Access Procedures 

ANA noted that paragraph (s) of the 

NPRM (77 FR 71723, December 4, 2012) 

identified certain Parts in the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–52A1153, 

dated July 13, 2011, for compliance with 

the proposed requirements. ANA stated 

that Part 2, which was not identified in 

paragraph (s) of the NPRM, provides 

access procedures. ANA questioned 

whether the AD required specific 

procedures for access. 

We agree, and have added new 

paragraph (u)(4) in this final rule to 

clarify that the access and restoration 

procedures specified in the referenced 

service information are not required by 

this AD. 

Request To Clarify Required Part 

References for Compliance 

ANA noted that paragraph (t) of the 

NPRM (77 FR 71723, December 4, 2012) 

referred to Parts 1, 3, 4, 7, and 8 of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–52A1153, 

dated July 13, 2011. Table 3 and Table 

4 of that service bulletin also refer to 

Parts 5 and 6 of that service bulletin. 

ANA questioned whether operators 

might do Part 5 and Part 6, which 

describe the preventive modification 

procedures, if no cracks are found. To 

avoid the need for requests for 

alternative methods of compliance 

(AMOCs) regarding this proposed 

requirement, ANA requested that we 

revise paragraph (t) of the NPRM to 

clarify that compliance is ‘‘in 

accordance with Parts 1, 2, 3, 4, 5, 6, 7, 

and 8’’ of that service bulletin. 

We disagree with the commenter. 

Paragraph (s) requires actions in 

accordance with Parts 5 and 6 of the 

Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–52A1153, 

dated July 13, 2011. Paragraph (t) of this 

AD requires other actions, done in 

accordance with Parts 1, 3, 4, 7, and 8 

of that service bulletin. We find it 

unnecessary to change this AD 

regarding this issue. 

Request To Exclude Certain 

Supplemental Structural Inspections 

Paragraph (v) of the NPRM (77 FR 

71723, December 4, 2012) would 

provide relief from certain supplemental 

structural inspections specified in 

Boeing Alert Service Bulletin 737– 

52A1153, dated July 13, 2011, and 

Boeing Alert Service Bulletin 737– 

52A1079, Revision 7, dated December 


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17, 2010. Boeing requested that we 

revise paragraph (v) of the NPRM to also 

provide relief from the supplemental 

structural inspections specified in Table 

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

Boeing Service Bulletin 737–52–1154, 

dated December 17, 2010. Boeing noted 

that the NPRM would require inspection 

of the adjacent cross beam if cracks are 

found in the lower cross beam, and 

repair of any cracked adjacent cross 

beam, in accordance with Boeing 

Service Bulletin 737–52–1154, dated 

December 17, 2010, but the damagetolerance inspections associated with 

that repair are not mentioned. 

We agree with the request. We have 

revised paragraph (v) in this final rule 

to also include reference to Table 5 of 

Boeing Service Bulletin 737–52–1154, 

dated December 17, 2010. 

Request To Delay Final Rule Pending 

Revised Service Information 

ANA stated that Boeing was in the 

process of revising Boeing Service 

Bulletins 737–52–1153 and 737–52– 

1154 based on ANA’s validation. ANA 

requested that we cite the revised 

service information, if it is available 

before the final rule is issued, to reduce 

additional burden for Boeing and the 

operators. Boeing reported that Boeing 

Service Bulletin 737–52–1154 was being 

revised to add extra material to the 

repair parts to address issues regarding 

repair kits found during the validation 

of the bulletin. 

We disagree to delay issuance of the 

final rule pending issuance of revised 

service information. Accomplishing the 

service information specified in this AD 

addresses the identified unsafe 

condition. When the revised service 

bulletins are presented to us for review, 

however, we might consider approving 

them as AMOCs for this AD. We have 

not changed this final rule regarding 

this issue. 

Additional Changes Made to This AD 

We have revised paragraph (v) and 

Note 2 to paragraph (v) of this final rule. 

We have designated paragraph (v) as 

paragraph (v)(1) of this final rule, and 

have reidentified Note 2 to paragraph (v) 

as paragraph (v)(2) of this final rule. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this 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 (77 FR 

71723, December 4, 2012) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (77 FR 71723, 

December 4, 2012). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

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 

Number of airplanes of U.S. 

registry 

Cost on U.S. operators 

Detailed inspection (retained action).2 work-hours × $85 per 

hour = $170 per inspection cycle.

$0 $170 per inspection cycle 494 $83,890 per inspection 

cycle. 

High frequency eddy current inspection (retained 

action).

4 work-hours × $85 per 

hour = $340 per inspection cycle.

0 $340 per inspection cycle 494 $167,960 per inspection 

cycle. 

Modification (retained action).144 work-hours × $85 

per hour = $12,240.

5,430 $17,670 ........................... 494 $8,728,980. 

Determination of door 

configuration (new action).

1 work-hour × $85 per 

hour = $85.

0 $85 .................................. 581 $49,385. 

Inspections (new action) .. 6 work-hours × $85 per 

hour = $510 per inspection cycle.

0 $510 per inspection cycle 581 $296,310 per inspection 

cycle. 

Modification (new action) 59 work-hours × $85 per 

hour = $5,015.

30,536 $35,551 ........................... * Unknown. 

* The number of airplanes that require this modification depends on no cracking being found during a certain inspection. 

We estimate the following costs to do 

any necessary related investigative and 

corrective actions 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 actions: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Related investigative and corrective actions ................ 59 work-hours × $85 per hour = $5,015 ...................... $30,536 $35,551 

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, 


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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) 

2000–06–13 R1, Amendment 39–12317 

(66 FR 36146, July 11, 2001), and adding 

the following new AD: 

2013–13–12 The Boeing Company: 

Amendment 39–17500 ; Docket No. 

FAA–2012–1156; Directorate Identifier 

2011–NM–205–AD. 

(a) Effective Date 

This AD is effective September 10, 2013. 

(b) Affected ADs 

This AD supersedes AD 2000–06–13 R1, 

Amendment 39–12317 (66 FR 36146, July 11, 

2001). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 737–200, –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 52, Doors. 

(e) Unsafe Condition 

This AD was prompted by reports of 

cracking in the forward and aft corner frame 

of the aft cargo door and in the lower cross 

beam. We are issuing this AD to prevent 

fatigue cracking of the corners of the door 

frame and the cross beams of the aft cargo 

door, which could result in rapid 

depressurization of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Affected Airplanes for Retained 

Paragraphs 

Paragraphs (h), (i), (j), (k), and (l) of this AD 

are restated from AD 2000–06–13 R1, 

Amendment 39–12317 (66 FR 36146, July 11, 

2001). These paragraphs apply to Model 737– 

200 and –200C series airplanes, line numbers 

6 through 873 inclusive; and Model 737–200, 

–200C, –300, and –400 series airplanes, line 

numbers 874 through 1642 inclusive; 

equipped with an aft cargo door having 

Boeing part number (P/N) 65–47952–1 or P/ 

N 65–47952–524, excluding airplanes 

identified in paragraphs (g)(1) and (g)(2) of 

this AD. 

(1) Those airplanes on which that door has 

been modified as specified in Boeing Service 

Bulletin 737–52–1079. Or, 

(2) Those airplanes on which the door 

assembly having P/N 65–47952–524 includes 

four straps (P/Ns 65–47952–139, 65–47952– 

140, 65–47952–141, and 65–47952–142) and 

a thicker lower cross beam web (P/N 65– 

47952–157). 

(h) Retained Inspections and Corrective 

Actions 

This paragraph restates the actions 

required by paragraph (a) of AD 2000–06–13 

R1, Amendment 39–12317 (66 FR 36146, July 

11, 2001), with revised service information. 

For airplanes identified in paragraph (g) of 

this AD: Within 90 days or 700 flight cycles 

after December 24, 1998 (the effective date of 

AD 98–25–06, Amendment 39–10931 (63 FR 

67769, December 9, 1998)), whichever occurs 

later, perform an internal detailed visual 

inspection to detect cracking of the corners 

of the door frame and the cross beams of the 

aft cargo door, in accordance with Boeing 

Service Bulletin 737–52–1079, Revision 5, 

dated May 16, 1996; Boeing Alert Service 

Bulletin 737–52A1079, Revision 6, dated 

November 18, 1999; or Boeing Alert Service 

Bulletin 737–52A1079, Revision 7, dated 

December 17, 2010. Accomplishment of the 

modification required by paragraph (l) of this 

AD constitutes terminating action for the 

repetitive inspection requirements of this 

paragraph. Doing the inspections required by 

paragraph (p) or (s) of this AD terminates the 

inspections required by this paragraph. 

(1) If no cracking is detected, accomplish 

the requirements of either paragraph (h)(1)(i) 

or (h)(1)(ii) of this AD. 

(i) Repeat the internal visual inspection 

thereafter at intervals not to exceed 4,500 

flight cycles. Or 

(ii) Prior to further flight, modify the 

corners of the door frame and the cross 

beams of the aft cargo door, in accordance 

with Boeing Service Bulletin 737–52–1079, 

Revision 5, dated May 16, 1996; Boeing Alert 

Service Bulletin 737–52A1079, Revision 6, 

dated November 18, 1999; or Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010. Accomplishment 

of such modification constitutes terminating 

action for the repetitive inspection 

requirements of paragraph (h)(1)(i) of this 

AD. 

(2) If any cracking is detected in the upper 

or lower cross beams, prior to further flight, 

modify the cracked beam, in accordance with 

Part I of the Accomplishment Instructions of 

Boeing Service Bulletin 737–52–1079, 

Revision 5, dated May 16, 1996; Part I of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 6, 

dated November 18, 1999; or Part II of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010. Accomplishment 

of such modification constitutes terminating 

action for the repetitive inspection 

requirements of paragraph (h)(1)(i) of this AD 

for the modified beam. 

(3) If any cracking is detected in the 

forward or aft upper door frame, prior to 

further flight, repair the frame and modify 

the corners of the door frame of the aft cargo 

door, in accordance with Part I of the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–52–1079, Revision 5, 

dated May 16, 1996; Part I of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 6, 

dated November 18, 1999; or Part II of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010; except as provided 

by paragraph (i) of this AD. Accomplishment 

of such modification constitutes terminating 

action for the repetitive inspection 

requirements of paragraph (h)(1)(i) of this AD 

for the upper door frame. 

(4) If any cracking is detected in the 

forward or aft lower door frame, prior to 

further flight, replace the damaged frame 

with a new frame, and modify the corners of 

the door frame of the aft cargo door, in 

accordance with Part I of the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–52–1079, Revision 5, 

dated May 16, 1996; Part I of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 6, 

dated November 18, 1999; or Part II of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010. Accomplishment 

of such modification constitutes terminating 


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action for the repetitive inspection 

requirements of paragraph (h)(1)(i) of this AD 

for the lower door frame. 

(i) Retained Exception for Certain Actions 

Specified in Paragraphs (h) and (l) of This 

AD 

This paragraph restates the requirement of 

paragraph (b) of AD 2000–06–13 R1, 

Amendment 39–12317 (66 FR 36146, July 11, 

2001). For actions required by paragraphs (h) 

and (l) of this AD: Where Boeing Service 

Bulletin 737–52–1079, Revision 5, dated May 

16, 1996; Boeing Alert Service Bulletin 737– 

52A1079, Revision 6, dated November 18, 

1999; or Boeing Alert Service Bulletin 737– 

52A1079, Revision 7, dated December 17, 

2010; specifies that certain repairs are to be 

accomplished in accordance with 

instructions received from Boeing, this AD 

requires that, prior to further flight, such 

repairs be accomplished 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 (x) of 

this AD. 

(j) Retained Corrective Actions for Certain 

Cracking Found During Inspection Required 

by Paragraph (h) of This AD 

This paragraph restates the corrective 

action required by paragraph (c) of AD 2000– 

06–13 R1, Amendment 39–12317 (66 FR 

36146, July 11, 2001), with revised service 

information. If any cracking of the outer 

chord of the upper or lower cross beams of 

the aft cargo door is detected during any 

inspection required by paragraph (h) of this 

AD, prior to further flight, accomplish the 

repair specified in paragraph (j)(1), (j)(2), 

(j)(3), or (j)(4) of this AD. For a repair method 

to be approved, as required by paragraphs 

(j)(1), (j)(3), and (j)(4) of this AD, the approval 

letter must specifically reference this AD. 

(1) Repair in accordance with a method 

approved by the Manager, Seattle ACO. 

(2) Repair in accordance with Boeing Alert 

Service Bulletin 737–52A1079, Revision 6, 

dated November 18, 1999; or Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010. 

(3) Repair in accordance with data meeting 

the type certification basis of the airplane 

approved by a Boeing Company Designated 

Engineering Representative who has been 

authorized by the FAA to make such 

findings. 

(4) Repair in accordance with a method 

approved by the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) whom we have 

authorized to make those findings. 

(k) Retained Inspections and Corrective 

Actions for Airplanes Identified in 

Paragraph (g) of This AD 

This paragraph restates the actions 

required by paragraph (d) of AD 2000–06–13 

R1, Amendment 39–12317 (66 FR 36146, July 

11, 2001), with revised service information. 

For airplanes identified in paragraph (g) of 

this AD: Within 4,500 flight cycles or 1 year 

after May 9, 2000 (the effective date of AD 

2000–06–13, Amendment 39–11654 (65 FR 

17583, April 4, 2000), whichever occurs later, 

perform a high frequency eddy current 

inspection (HFEC) to detect cracking of the 

four corners of the door frame of the aft cargo 

door, using a method approved in accordance 

with the procedures specified in paragraph 

(x) of this AD, or in accordance with Boeing 

Alert Service Bulletin 737–52A1079, 

Revision 6, dated November 18, 1999; or 

Boeing Alert Service Bulletin 737–52A1079, 

Revision 7, dated December 17, 2010. 

Accomplishment of the modification 

required by paragraph (l) of this AD 

constitutes terminating action for the 

repetitive inspection requirements of this 

paragraph. Doing the inspections required by 

paragraph (p) or (s) of this AD terminates the 

inspections required by this paragraph. 

Note 1 to paragraph (k) of this AD: 

Additional guidance for the inspection can 

be found in Boeing 737 Nondestructive Test 

Manual, Part 6, Chapter 51–00–00 (Figure 4 

or Figure 23). 

(1) If no cracking of the corners of the door 

frame of the aft cargo door is detected, repeat 

the HFEC inspections thereafter at intervals 

not to exceed 4,500 flight cycles until 

accomplishment of the modification 

specified in paragraph (l) of this AD. 

(2) If any cracking of the corners of the 

door frame of the aft cargo door is detected, 

prior to further flight, replace the damaged 

frame with a new frame, and modify the four 

corners of the door frame, in accordance with 

Part II and Part III of the Accomplishment 

Instructions of Boeing Service Bulletin 737– 

52–1079, Revision 5, dated May 16, 1996; 

Part II and Part III of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–52A1079, Revision 6, dated November 

18, 1999; or Part III and Part IV of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010. Accomplishment 

of such modification constitutes terminating 

action for the repetitive inspection 

requirements of paragraph (k)(1) of this AD 

for that door frame. 

(l) Retained Terminating Action for 

Inspections Specified in Paragraphs (h) and 

(k) of This AD 

This paragraph restates the action required 

by paragraph (e) of AD 2000–06–13 R1, 

Amendment 39–12317 (66 FR 36146, July 11, 

2001), with revised service information. For 

airplanes identified in paragraph (g) of this 

AD: Within 4 years or 12,000 flight cycles 

after August 15, 2001 (the effective date of 

AD 2000–06–13 R1), whichever occurs later, 

modify the four corners of the door frame and 

the cross beams of the aft cargo door, in 

accordance with Part II of the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–52–1079, Revision 5, 

dated May 16, 1996; Part II of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 6, 

dated November 18, 1999; or Part III of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010. Accomplishment 

of that modification constitutes terminating 

action for the repetitive inspection 

requirements of paragraphs (h) and (k) of this 

AD. 

(m) Retained Method of Compliance 

This paragraph restates the method of 

compliance of Note 3 of AD 2000–06–13 R1, 

Amendment 39–12317 (66 FR 36146, July 11, 

2001). Accomplishment of the modification 

required by paragraph (a) of AD 90–06–02, 

Amendment 39–6489 (55 FR 8372, March 7, 

1990), is considered acceptable for 

compliance with the requirements of 

paragraph (l) of this AD. 

(n) Retained Credit for Previous Actions 

This paragraph restates the credit given for 

service information specified in Note 4 of AD 

2000–06–13 R1, Amendment 39–12317 (66 

FR 36146, July 11, 2001). This paragraph 

provides credit for the modification of the 

corners of the door frame and the cross 

beams of the aft cargo door required by 

paragraph (l) of this AD, if the modification 

was accomplished prior to August 15, 2001 

(the effective date of AD 2000–06–13 R1), 

using Boeing Service Bulletin 737–52–1079, 

dated December 16, 1983; Revision 1, dated 

December 15, 1988; Revision 2, dated July 20, 

1989; Revision 3, dated May 17, 1990; or 

Revision 4, dated February 21, 1991. 

(o) New Requirement for Determining Door 

Configuration 

At the applicable time specified in Table 

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

Alert Service Bulletin 737–52A1153, dated 

July 13, 2011, except as provided by 

paragraph (u)(1) of this AD: Inspect to 

determine the configuration of the aft cargo 

door, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1153, dated July 13, 

2011. A review of airplane maintenance 

records is acceptable in lieu of this 

inspection if the configuration of the cargo 

door can be conclusively determined from 

that review. 

(p) New Requirements for Certain Doors 

Subject to Boeing Alert Service Bulletin 737– 

52A1079, Revision 7, Dated December 17, 

2010 

If, during the inspection required by 

paragraph (o) of this AD, any door is 

determined to be from any airplane having 

line numbers 6 through 873 inclusive, and 

neither the modification nor the repair 

specified in any service bulletin identified in 

paragraphs (p)(1) through (p)(7) of this AD 

has been done as of the effective date of this 

AD: Do a one-time HFEC and a one-time 

ultrasonic inspection for cracking of the 

upper and lower corner frames and the upper 

and lower cross beams, and do all applicable 

related investigative and corrective actions, 

in accordance with Parts II, III, IV, and VI of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–52A1079, 

Revision 7, dated December 17, 2010; and, as 

applicable, the Accomplishment Instructions 

of Boeing Special Attention Service Bulletin 

737–52–1154, dated December 17, 2010, as 

revised by Boeing Special Attention Service 

Bulletin 737–52–1154, Revision 1, dated 

August 3, 2011; except as provided by 

paragraphs (u)(2) and (u)(3) of this AD. Do 

the inspections before the accumulation of 

27,000 total flight cycles on the door, or 

within 4,500 door flight cycles after the 


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47554 Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 

effective date of this AD, whichever occurs 

later (for airplanes on which the door flight 

cycles are known); or within 4,500 flight 

cycles after the effective date of this AD (for 

airplanes on which door flight cycles are not 

known). Do all applicable related 

investigative and corrective actions before 

further flight. If no cracking is found during 

the initial inspections, before further flight, 

do the modification in accordance with Part 

III of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–52A1079, 

Revision 7, dated December 17, 2010. Doing 

the inspection specified in this paragraph 

terminates the inspections required by 

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

(1) Boeing Service Bulletin 737–52–1079, 

dated December 16, 1983. 

(2) Boeing Service Bulletin 737–52–1079, 

Revision 1, dated December 15, 1988. 

(3) Boeing Service Bulletin 737–52–1079, 

Revision 2, dated July 20, 1989. 

(4) Boeing Service Bulletin 737–52–1079, 

Revision 3, dated May 17, 1990. 

(5) Boeing Service Bulletin 737–52–1079, 

Revision 4, dated February 21, 1991. 

(6) Boeing Service Bulletin 737–52–1079, 

Revision 5, dated May 16, 1996. 

(7) Boeing Service Bulletin 737–52A1079, 

Revision 6, dated November 18, 1999. 

(q) Requirements for All Doors Subject to 

Boeing Alert Service Bulletin 737–52A1079, 

Revision 7, Dated December 17, 2010 

If, during the inspection required by 

paragraph (o) of this AD, any door is 

determined to be from any airplane having 

line numbers 6 through 873 inclusive: Before 

the accumulation of 27,000 total flight cycles 

on the door, or within 4,500 door flight 

cycles after the effective date of this AD, 

whichever occurs later, (for airplanes on 

which the door flight cycles are known); or 

within 4,500 flight cycles after the effective 

date of this AD (for airplanes on which door 

flight cycles are not known); inspect the 

lower corner frames to determine if the door 

has reinforcement angles, P/N 65C25180–9, 

–43, –10, –11, or –12, that were installed as 

specified in any service bulletin identified in 

paragraphs (q)(1) through (q)(5) of this AD. If 

any affected reinforcement angle is found, do 

a one-time general visual inspection for edge 

margin and do a detailed inspection for 

cracks; in accordance with Part V of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010. 

(1) Boeing Service Bulletin 737–52–1079, 

dated December 16, 1983. 

(2) Boeing Service Bulletin 737–52–1079, 

Revision 1, dated December 15, 1988. 

(3) Boeing Service Bulletin 737–52–1079, 

Revision 2, dated July 20, 1989. 

(4) Boeing Service Bulletin 737–52–1079, 

Revision 3, dated May 17, 1990. 

(5) Boeing Service Bulletin 737–52–1079, 

Revision 4, dated February 21, 1991. 

(r) Corrective Actions for Inspections 

Specified in Paragraph (q) of This AD 

If, during any inspection required by 

paragraph (q) of this AD, any crack is found, 

or if any edge margin does not meet the 

specification identified in Part V of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010, before further 

flight, do the actions specified in paragraphs 

(r)(1), (r)(2), and (r)(3) of this AD. 

(1) Replace the corner reinforcement angle, 

in accordance with Part III of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1079, Revision 7, 

dated December 17, 2010. 

(2) Do a one-time detailed inspection or 

HFEC inspection for cracking at the forward 

and aft ends of cross beam D, in accordance 

with Part 1 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–52–1154, dated 

December 17, 2010; or Boeing Special 

Attention Service Bulletin 737–52–1154, 

dated December 17, 2010, as revised by 

Boeing Special Attention Service Bulletin 

737–52–1154, Revision 1, dated August 3, 

2011. If any cracking is found, before further 

flight, do all applicable repairs in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–52–1154, dated December 17, 2010; or 

Boeing Special Attention Service Bulletin 

737–52–1154, dated December 17, 2010, as 

revised by Boeing Special Attention Service 

Bulletin 737–52–1154, Revision 1, dated 

August 3, 2011, except as provided by 

paragraph (u)(2) of this AD. 

(3) Do a one-time detailed inspection or 

ultrasonic inspection for cracking on the 

frames, in accordance with Part 2 (detailed 

inspection) or Part 8 (ultrasonic inspection) 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

737–52–1154, dated December 17, 2010, as 

revised by Boeing Special Attention Service 

Bulletin 737–52–1154, Revision 1, dated 

August 3, 2011. If any cracking is found, 

before further flight, replace the frame in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–52A1079, Revision 7, dated December 

17, 2010. 

(s) Requirements for Doors Subject to Boeing 

Alert Service Bulletin 737–52A1153, Dated 

July 13, 2011 

If, during the action required by paragraph 

(o) of this AD, a door is determined to be 

from an airplane having line numbers 874 

and subsequent: At the applicable time 

specified in Tables 1 and 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–52A1153, dated July 13, 2011, 

except as provided by paragraph (u)(1) of this 

AD, do high frequency and detailed 

inspections for cracks in the forward and aft 

ends of cross beam E, and do all applicable 

related investigative and corrective actions, 

in accordance with Parts 1, 3, 4, 5, and 6 of 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 737–52A1153, dated 

July 13, 2011; and, as applicable, the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–52– 

1154, dated December 17, 2010, as revised by 

Boeing Special Attention Service Bulletin 

737–52–1154, Revision 1, dated August 3, 

2011; except as provided by paragraph (u)(2) 

of this AD. Do all applicable related 

investigative and corrective actions at the 

applicable time specified in Tables 1 and 2 

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

Alert Service Bulletin 737–52A1153, dated 

July 13, 2011, except as provided by 

paragraph (u)(1) of this AD. If no cracking is 

found during the inspections specified in 

Boeing Alert Service Bulletin 737–52A1153, 

dated July 13, 2011, at the applicable time 

specified in Tables 1 and 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–52A1153, dated July 13, 2011, 

except as provided by paragraph (u)(1) of this 

AD, do the modification in accordance with 

Parts 5 and 6, as applicable, of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1153, dated July 13, 

2011. Repeat the inspections thereafter at the 

times specified in Tables 1 and 2 of 

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

Alert Service Bulletin 737–52A1153, dated 

July 13, 2011, until the preventative 

modification or repair is done to both ends 

of cross beam E in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–52A1153, dated July 13, 

2011. Doing the inspection specified in this 

paragraph terminates the inspections 

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

(t) One Time Inspections for Doors Subject 

to Boeing Alert Service Bulletin 737– 

52A1153, Dated July 13, 2011 

If, during the actions required by paragraph 

(o) of this AD, a door is determined to be 

from an airplane having line numbers 874 

and subsequent: At the applicable time 

specified in Tables 3 and 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–52A1153, dated July 13, 2011, 

except as provided by paragraph (u)(1) of this 

AD, do a one-time ultrasonic inspection of 

the frame and a detailed inspection of the 

reinforcing angle for cracks of the forward 

and aft ends of cross beam E, and do all 

applicable related investigative and 

corrective actions, in accordance with Parts 

1, 3, 4, 7, and 8 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–52A1153, dated July 13, 2011; and, as 

applicable; the Accomplishment Instructions 

of Boeing Special Attention Service Bulletin 

737–52–1154, dated December 17, 2010, as 

revised by Boeing Special Attention Service 

Bulletin 737–52–1154, Revision 1, dated 

August 3, 2011; except as provided by 

paragraph (u)(2) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. 

(u) Service Information Exceptions 

The following exceptions apply to this AD. 

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

Boeing Alert Service Bulletin 737–52A1153, 

dated July 13, 2011, specifies a compliance 

time ‘‘after the original issue date of this 

service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(2) Where Boeing Special Attention Service 

Bulletin 737–52–1154, dated December 17, 

2010; and Boeing Special Attention Service 

Bulletin 737–52–1154, dated December 17, 

2010, as revised by Boeing Special Attention 

Service Bulletin 737–52–1154, Revision 1, 

dated August 3, 2011, specify to contact 

Boeing for repair, before further flight, repair 

using a method approved in accordance with 

the procedures specified in paragraph (x) of 

this AD. 


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Federal Register / Vol. 78, No. 151 / Tuesday, August 6, 2013 / Rules and Regulations 47555 

(3) Where Boeing Alert Service Bulletin 

737–52A1079, Revision 7, dated December 

17, 2010, specifies to contact Boeing for 

repair, before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (x) of this 

AD. 

(4) This AD does not require 

accomplishment of the access and restoration 

procedures identified in the Work 

Instructions of Boeing Alert Service Bulletin 

737–52A1079, Revision 7, dated December 

17, 2010; Boeing Alert Service Bulletin 737– 

52A1153, dated July 13, 2011; Boeing Special 

Attention Service Bulletin 737–52–1154, 

dated December 17, 2010; and Boeing Special 

Attention Service Bulletin 737–52–1154, 

dated December 17, 2010, as revised by 

Boeing Special Attention Service Bulletin 

737–52–1154, Revision 1, dated August 3, 

2011. 

(v) Supplemental Structural Inspections 

(1) The supplemental structural 

inspections specified in Tables 5 and 6 of 

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

Alert Service Bulletin 737–52A1153, dated 

July 13, 2011; and Tables 3 and 4 of 

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

Alert Service Bulletin 737–52A1079, 

Revision 7, dated December 17, 2010; and 

Table 5 of paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Service Bulletin 737–52–1154, dated 

December 17, 2010, as revised by Boeing 

Special Attention Service Bulletin 737–52– 

1154, Revision 1, dated August 3, 2011, are 

not required by this AD. 

(2) The damage tolerance inspections 

specified in Tables 5 and 6 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–52A1153, dated July 13, 2011; 

and Tables 3 and 4 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–52A1079, Revision 7, dated 

December 17, 2010; and Table 5 of paragraph 

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

Bulletin 737–52–1154, dated December 17, 

2010, as revised by Boeing Special Attention 

Service Bulletin 737–52–1154, Revision 1, 

dated August 3, 2011; may be used in 

support of compliance with section 

121.1109(c)(2) or 129.109(b)(2) of the Federal 

Aviation Regulations (14 CFR 121.1109(c)(2) 

or 14 CFR 129.109(b)(2)). The corresponding 

actions specified in the Accomplishment 

Instructions and figures of Boeing Alert 

Service Bulletin 737–52A1153, dated July 13, 

2011; and Boeing Alert Service Bulletin 737– 

52A1079, Revision 7, dated December 17, 

2010; are not required by this AD. 

(w) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraphs (p), (q), and 

(r) of this AD, if the actions were 

accomplished before the effective date of this 

AD using any service information specified 

in paragraph (w)(1)(i), (w)(1)(ii), (w)(1)(iii), 

(w)(1)(iv), (w)(1)(v), (w)(1)(vi), or (w)(1)(vii) 

of this AD. 

(i) Boeing Service Bulletin 737–52–1079, 

dated December 16, 1983. 

(ii) Boeing Service Bulletin 737–52–1079, 

Revision 1, dated December 15, 1988. 

(iii) Boeing Service Bulletin 737–52–1079, 

Revision 2, dated July 20, 1989. 

(iv) Boeing Service Bulletin 737–52–1079, 

Revision 3, dated May 17, 1990. 

(v) Boeing Service Bulletin 737–52–1079, 

Revision 4, dated February 21, 1991. 

(vi) Boeing Service Bulletin 737–52–1079, 

Revision 5, dated May 16, 1996. 

(vii) Boeing Alert Service Bulletin 737– 

52A1079, Revision 6, dated November 18, 

1999. 

(2) This paragraph provides credit for 

actions required by paragraphs (s) and (t) of 

this AD, if the actions were accomplished 

before the effective date of this AD using 

Boeing Service Bulletin 737–52–1154, dated 

December 17, 2010, provided that any 

alternative detailed inspections specified in 

Part 17 of the Accomplishment Instructions 

of Boeing Service Bulletin 737–52–1154, 

dated December 17, 2010, were done in 

accordance with Part 11 of the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–52–1154, dated 

December 17, 2010. 

(x) 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, 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 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 2000–06–13, 

Amendment 39–11654 (65 FR 17583, April 4, 

2000); and AD 2000–06–13 R1, Amendment 

39–12317 (66 FR 36146, July 11, 2001); are 

approved as AMOCs for the corresponding 

requirements of this AD. 

(y) Related Information 

For more information about this AD, 

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. 

(z) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on September 10, 2013. 

(i) Boeing Alert Service Bulletin 737– 

52A1153, dated July 13, 2011. 

(ii) Boeing Alert Service Bulletin 737– 

52A1079, Revision 7, dated December 17, 

2010. 

(iii) Boeing Special Attention Service 

Bulletin 737–52–1154, dated December 17, 

2010. 

(iv) Boeing Special Attention Service 

Bulletin 737–52–1154, Revision 1, dated 

August 3, 2011. 

(4) The following service information was 

approved for IBR on May 9, 2000 (65 FR 

17583, April 4, 2000). 

(i) Boeing Alert Service Bulletin 737– 

52A1079, Revision 6, dated November 18, 

1999. 

(ii) Reserved. 

(5) The following service information was 

approved for IBR on December 24, 1998 (63 

FR 67769, December 9, 1998). 

(i) Boeing Service Bulletin 737–52–1079, 

Revision 5, dated May 16, 1996. 

(ii) Reserved. 

(6) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

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

Internet https://www.myboeingfleet.com. 

(7) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

(8) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on June 18, 

2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–18765 Filed 8–5–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HOMELAND 

SECURITY 

Coast Guard 

33 CFR Parts 100 and 165 

[Docket No. USCG–2012–1057] 

RIN 1625–AA08; AA00 

Special Local Regulations and Safety 

Zones; Recurring Events in Northern 

New England 

AGENCY: Coast Guard, DHS. 


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