Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 31389 

time specified in paragraph (m)(1) or (m)(2) 

of this AD. 

(1) If the inspection is done on or after the 

effective date of this AD: Submit the report 

within 90 days after doing the inspection. 

(2) If the inspection was done prior to the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(n) 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: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1138; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. AMOCs approved previously in 

accordance with AD 2010–02–10, 

Amendment 39–16181 (75 FR 4477, January 

28, 2010), are approved as AMOCs for the 

corresponding provisions of this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing, and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(o) Special Flight Permits 

Special flight permits, as described in 

Section 21.197 and Section 21.199 of the 

Federal Aviation Regulations (14 CFR 21.197 

and 21.199), are not allowed if any crack is 

found during any inspection required by this 

AD. 

(p) Related Information 

(1) Refer to mandatory continued 

airworthiness information (MCAI) EASA 

Airworthiness Directive 2011–0211, dated 

October 31, 2011, and the service information 

specified in paragraphs (p)(1)(i) through 

(p)(1)(vii) of this AD, for related information. 

(i) Airbus Mandatory Service Bulletin 

A330–32–3220, dated October 10, 2008. 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 01, dated October 5, 

2011. 

(iii) Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 02, dated December 

13, 2012. 

(iv) Airbus Mandatory Service Bulletin 

A330–32–3248, Revision 01, including 

Appendix 01, dated December 13, 2012. 

(v) Airbus Mandatory Service Bulletin 

A340–32–4264, dated October 10, 2008. 

(vi) Airbus Mandatory Service Bulletin 

A340–32–4286, dated October 5, 2011. 

(vii) Airbus Mandatory Service Bulletin 

A340–32–5087, dated October 10, 2008. 

(2) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

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

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. You may 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

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

(q) 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 June 28, 2013. 

(i) Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 01, dated October 5, 

2011. 

(ii) Airbus Mandatory Service Bulletin 

A330–32–3220, Revision 02, dated December 

13, 2012. 

(iii) Airbus Mandatory Service Bulletin 

A330–32–3248, Revision 01, including 

Appendix 01, dated December 13, 2012. 

(iv) Airbus Mandatory Service Bulletin 

A340–32–4286, dated October 5, 2011. 

(4) The following service information was 

approved for IBR on March 4, 2010 (75 FR 

4477, January 28, 2010). 

(i) Airbus Mandatory Service Bulletin 

A330–32–3220, dated October 10, 2008. 

(ii) Airbus Mandatory Service Bulletin 

A340–32–4264, dated October 10, 2008. 

(iii) Airbus Mandatory Service Bulletin 

A340–32–5087, dated October 10, 2008. 

(5) For service information identified in 

this AD, contact Airbus SAS—Airworthiness 

Office—EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone +33 

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

airworthiness.A330-A340@airbus.com; 

Internet http://www.airbus.com. 

(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 May 13, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–11903 Filed 5–23–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0855; Directorate 

Identifier 2011–NM–136–AD; Amendment 

39–17452; AD 2013–09–10] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding an 

existing airworthiness directive (AD) for 

all The Boeing Company Model 737– 

100, –200, –200C, –300, –400, and –500 

series airplanes. That AD currently 

requires repetitive inspections to detect 

cracking of the lower corners of the door 

frame and cross beam of the forward 

cargo door, and corrective actions if 

necessary. That AD also requires 

eventual modification of the outboard 

radius of the lower corners of the door 

frame and reinforcement of the cross 

beam of the forward cargo door, which 

terminates the existing repetitive 

inspections. This new AD revises the 

compliance times for the preventive 

modification; adds certain inspections 

for cracks in the number 5 cross beam 

of the forward cargo door; and adds 

inspections of the number 4 cross beam 

if cracks are found in the number 5 

cross beam, and corrective actions if 

necessary. For certain airplanes, this 

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31390 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 

new AD also adds a one-time inspection 

for airplanes previously modified or 

repaired, and a one-time inspection of 

the reinforcement angle for excessive 

shimming or fastener pull-up, and 

corrective actions if necessary. This AD 

was prompted by additional reports of 

fatigue cracking in the radius of the 

lower frames and in the lower number 

5 cross beam of the forward cargo door. 

We are issuing this AD to prevent 

fatigue cracking of the lower corners of 

the door frame and number 5 cross 

beam of the forward cargo door, which 

could result in rapid depressurization of 

the airplane. 

DATES: This AD is effective June 28, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of June 28, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of May 16, 2000 (65 FR 

19302, April 11, 2000). 

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 

directive (AD) 2000–07–06, Amendment 

39–11660 (65 FR 19302, April 11, 2000). 

That AD applies to the specified 

products. The NPRM published in the 

Federal Register on August 21, 2012 (77 

FR 50407). The NPRM proposed to 

continue to require repetitive 

inspections to detect cracking of the 

lower corners of the door frame and 

cross beam of the forward cargo door, 

and corrective actions if necessary. The 

NPRM also proposed to continue to 

require eventual modification of the 

outboard radius of the lower corners of 

the door frame and reinforcement of the 

cross beam of the forward cargo door, 

which would constitute terminating 

action for the existing repetitive 

inspections. Additionally, the NPRM 

proposed to revise the compliance times 

for the preventive modification; add 

certain inspections for cracks in the 

number 5 cross beam of the forward 

cargo door; and add inspections of the 

number 4 cross beam if cracks are found 

in the number 5 cross beam, and 

corrective actions if necessary. For 

certain airplanes, the NPRM also 

proposed to add a one-time inspection 

for airplanes previously modified or 

repaired, and a one-time inspection of 

the reinforcement angle for excessive 

shimming or fastener pull-up, and 

corrective actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 50407, 

August 21, 2012) and the FAA’s 

response to each comment. 

Comment Regarding Winglet 

Supplemental Type Certificate (STC) 

Aviation Partners Boeing stated that 

installation of winglets per STC 

ST01219SE (http://rgl.faa.gov/

regulatory_and_guidance_library/rgstc.

nsf/0/2C6E3DBDDD36F91C862576

A4005D64E2?OpenDocument&

Highlight=st01219se) does not affect the 

ability to accomplish the service 

information or the NPRM (77 FR 50407, 

August 21, 2012). 

We have revised paragraph (c) in this 

final rule, by adding new paragraph 

(c)(2), to state that installation of STC 

ST01219SE (http://rgl.faa.gov/ 

regulatory_and_guidance_library/ 

rgstc.nsf/0/2C6E3DBDDD36F9

1C862576A4005D64E2?Open

Document&Highlight=st01219se) does 

not affect the ability to accomplish the 

actions required by this AD. Therefore, 

for airplanes on which STC ST01219SE 

is installed, a ‘‘change in product’’ 

AMOC approval request is not necessary 

to comply with the requirements of 14 

CFR 39.17. For all other AMOC 

requests, however, the operator must 

request approval for an AMOC in 

accordance with the procedures 

specified in paragraph (n) of this AD. 

Request To Add New Requirements 

Boeing asked that we add a new 

paragraph (k) to the NPRM (77 FR 

50407, August 21, 2012) titled ‘‘New 

Inspections and Corrective Actions to 

Ensure Cross Beam Reinforcement,’’ and 

suggested language for that new 

requirement. Boeing stated that the 

intent of the NPRM and Boeing Alert 

Service Bulletin 737–52A1100, Revision 

5, dated February 14, 2011, is to ensure 

that all forward cargo doors have the 

reinforcing modifications installed on 

both the beam and the frame at the 

forward and aft lower corners of the 

door. Boeing added that the current 

language in the NPRM and this service 

information leave open the potential 

that some doors might not have the 

reinforcing modification on the aft end 

of the cross beam, even though the 

doors were modified as specified in 

Boeing Service Bulletin 737–52–1100, 

dated August 25, 1988, or Revision 1, 

dated July 20, 1989; or in accordance 

with the requirements of AD 90–06–02, 

Amendment 39–6489 (55 FR 8372, 

March 7, 1990). 

We do not agree with the commenter’s 

request to add a new requirement to this 

AD. Boeing Service Bulletin 737–52– 

1100, dated August 25, 1988; and 

Revision 1, dated July 20, 1989; 

includes modifications of the forward 

corner of the door frame and forward 

end of the lower cross beam, but no 

modifications of the aft end of the door. 

Modifications of the aft corner of the 

door frame and aft end of the lower 

cross beam were added in Boeing 

Service Bulletin 737–52–1100, Revision 

2, dated March 31, 1994. Boeing Service 

Bulletin 737–52–1100, Revision 2, dated 

March 31, 1994, was required by 

paragraph (c) of AD 2000–07–06, 

Amendment 39–11660 (65 FR 19302, 

April 11, 2000), as terminating action 

for the repetitive inspections. Paragraph 

(c) of AD 2000–07–06 is restated in 

paragraph (i) of this AD, and addresses 

airplanes on which no modification was 

accomplished previously. 

The intent of paragraph (d) of AD 

2000–07–06, Amendment 39–11660 (65 

FR 19302, April 11, 2000), which is 

restated in paragraph (j) of this AD, was 

to address airplanes on which a 

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Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 31391 

modification was previously 

accomplished in accordance with 

Boeing Service Bulletin 737–52–1100, 

dated August 25, 1988; or Revision 1, 

dated July 20, 1989; and to ensure that 

both the forward and aft ends of the 

lower beam of the door were modified, 

as well as the forward and aft corners of 

the door frame. Therefore, Boeing 

Service Bulletin 737–52–1100, Revision 

2, dated March 31, 1994, was required 

by AD 2000–07–06 for those 

modifications. However, paragraph (d) 

of AD 2000–07–06 and paragraph (j) of 

this AD do not specify modifying the aft 

end of the lower beam. 

We have made no change to the AD 

in regard to Boeing’s request. However, 

we are considering proposing additional 

rulemaking in the near future to address 

this issue. 

Explanation of Change to Final Rule 

We have changed paragraph (g) of this 

final rule to specify performing the 

inspection in accordance with Boeing 

737 Nondestructive Test (NDT) Manual, 

D6–37239, Part 6, Section 51–00–00, 

Procedure 4 or Procedure 23, Revision 

108, dated November 15, 2012, as 

applicable. The subject procedures were 

referred to as figures in the NPRM (77 

FR 50407, August 21, 2012). Because of 

a publishing system change in this 

revision of the NDT manual, the term 

‘‘figure’’ was changed to ‘‘procedure.’’ 

The technical instructions in the NDT 

manual were not changed. 

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 change described previously. 

We also determined that this change 

will not increase the economic burden 

on any operator or increase the scope of 

the 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 Cost on U.S. 

operators 

Inspections retained from AD 

2000–07–06, Amendment 

39–11660 (65 FR 19302, 

April 11, 2000).

1 work-hour × $85 per hour = 

$85 per inspection cycle.

$0 $85 per inspection cycle ........ $49,385 per inspection cycle. 

Modification retained from AD 

2000–07–06.

18 work-hours × $85 per hour 

= $1,530.

$1,865 $3,395 .................................... $1,972,495. 

Inspections, new action .......... 9 work-hours × $85 per hour 

= $765.

$0 $765 ....................................... $444,465. 

We estimate the following costs to do 

any necessary modifications 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 modifications: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Modification ................................................................... 84 work-hours × $85 per hour = $7,140 ...................... $12,395 $19,535 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition repairs/ 

replacements specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We 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 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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: 

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31392 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2000–07–06, Amendment 39–11660 (65 

FR 19302, April 11, 2000), and adding 

the following new AD: 

2013–09–10 The Boeing Company: 

Amendment 39–17452; Docket No. 

FAA–2012–0855; Directorate Identifier 

2011–NM–136–AD. 

(a) Effective Date 

This AD is effective June 28, 2013. 

(b) Affected ADs 

This AD supersedes AD 2000–07–06, 

Amendment 39–11660 (65 FR 19302, April 

11, 2000). 

(c) Applicability 

(1) This AD applies to all The Boeing 

Company Model 737–100, –200, –200C, 

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

certificated in any category. 

(2) Installation of Supplemental Type 

Certificate (STC) ST01219SE (http://rgl.faa.

gov/regulatory_and_guidance_library/rgstc

.nsf/0/2C6E3DBDDD36F91C862576A40

05D64E2?OpenDocument&Highlight=

st01219se) does not affect the ability to 

accomplish the actions required by this AD. 

Therefore, for airplanes on which STC 

ST01219SE is installed, a ‘‘change in 

product’’ alternative method of compliance 

(AMOC) approval request is not necessary to 

comply with the requirements of 14 CFR 

39.17. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 52, Doors. 

(e) Unsafe Condition 

This AD was prompted by additional 

reports of fatigue cracking in the radius of the 

lower frames and in the lower number 5 

cross beam of the forward cargo door. We are 

issuing this AD to prevent fatigue cracking of 

the lower corners of the door frame and 

number 5 cross beam of the forward 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) Retained High Frequency Eddy Current 

(HFEC) Initial/Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (a) of AD 2000–07–06, 

Amendment 39–11660 (65 FR 19302, April 

11, 2000), with revised service information. 

Within 1 year or 4,500 flight cycles after May 

16, 2000 (the effective date of AD 2000–07– 

06), whichever occurs later, perform an HFEC 

inspection to detect cracking of the lower 

corners (forward and aft) of the door frame 

of the forward cargo door, in accordance with 

Figure 4 or Figure 23, of Section 51–00–00, 

of Part 6, of Boeing 737 Nondestructive Test 

(NDT) Manual, D6–37239, dated August 5, 

1997, as applicable; or Procedure 4 or 

Procedure 23, of Section 51–00–00, of Part 6, 

of Boeing 737 Nondestructive Test (NDT) 

Manual, D6–37239, Revision 108, dated 

November 15, 2012; as applicable. 

Note 1 to paragraphs (g), (h), (i), and (j) of 

this AD: Accomplishment of Boeing Service 

Bulletin 737–52–1100, Revision 2, dated 

March 31, 1994, does not supersede the 

requirements of AD 90–06–02, Amendment 

39–6489 (55 FR 8372, March 7, 1990). 

(1) If no cracking is detected, repeat the 

HFEC inspection thereafter at intervals not to 

exceed 4,500 flight cycles, until the 

requirements of paragraph (i) of this AD have 

been accomplished. 

(2) If any cracking is detected during any 

inspection required by paragraph (g) of this 

AD, prior to further flight, accomplish the 

requirements of paragraphs (g)(2)(i) and 

(g)(2)(ii) of this AD, which constitute 

terminating action for the repetitive 

inspections required by paragraph (g)(1) of 

this AD. 

(i) Accomplish the requirements of 

paragraph (g)(2)(i)(A) or (g)(2)(i)(B) of this 

AD, and install a cross beam repair and 

reinforcement modification of the cross 

beam, in accordance with Boeing Service 

Bulletin 737–52–1100, Revision 2, dated 

March 31, 1994. 

(A) Repair the door frame of the forward 

cargo door in accordance with a method 

approved by the Manager, Seattle Aircraft 

Certification Office (ACO), Transport 

Airplane Directorate, FAA; or in accordance 

with data meeting the type certification basis 

of the airplane approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make such findings. For a repair or 

modification method to be approved by the 

Manager, Seattle ACO, as required by this 

paragraph, and paragraphs (g)(2)(ii), (h)(2), 

(h)(3)(ii), and (i)(2) of this AD, the Manager’s 

approval letter must specifically reference 

this AD. 

(B) Replace the door frame of the forward 

cargo door with a new door frame, in 

accordance with Boeing Service Bulletin 

737–52–1100, Revision 2, dated March 31, 

1994. 

(ii) Modify the repaired or replaced door 

frame of the forward cargo door, in 

accordance with a method approved by the 

Manager, Seattle ACO, or in accordance with 

data meeting the type certification basis of 

the airplane approved by the Boeing 

Commercial Airplanes ODA that has been 

authorized by the Manager, Seattle ACO, to 

make those findings. 

(h) Retained Initial Detailed Inspection and 

Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (b) of AD 2000–07–06, 

Amendment 39–11660 (65 FR 19302, April 

11, 2000). Within 1 year or 4,500 flight cycles 

after May 16, 2000 (the effective date of AD 

2000–07–06), whichever occurs later, 

perform a detailed inspection to detect 

cracking of the cross beam (i.e., upper and 

lower chord and web sections) of the forward 

cargo door, in accordance with Boeing 

Service Bulletin 737–52–1100, Revision 2, 

dated March 31, 1994. For the purposes of 

this AD, a detailed inspection is: An 

intensive examination of a specific item, 

installation, or assembly to detect damage, 

failure, or irregularity. Available lighting is 

normally supplemented with a direct source 

of good lighting at an intensity deemed 

appropriate. Inspection aids such as mirror, 

magnifying lenses, etc., may be necessary. 

Surface cleaning and elaborate procedures 

may be required. 

(1) If no cracking is detected, repeat the 

inspection thereafter at intervals not to 

exceed 4,500 flight cycles until the 

requirements of paragraph (i) of this AD have 

been accomplished. 

(2) If any cracking is detected on the lower 

chord section of the cross beam during any 

inspection required by paragraph (h) of this 

AD, prior to further flight, repair in 

accordance with a method approved by the 

Manager, Seattle ACO, or in accordance with 

data meeting the type certification basis of 

the airplane approved by the Boeing 

Commercial Airplanes ODA that has been 

authorized by the Manager, Seattle ACO, to 

make those findings. 

(3) If any cracking is detected on any area 

excluding the lower chord section of the 

cross beam (i.e., upper chord and web 

section) during any inspection required by 

paragraph (h) of this AD, prior to further 

flight, accomplish the requirements of 

paragraph (h)(3)(i) or (h)(3)(ii) of this AD, as 

applicable, which constitutes terminating 

action for the repetitive inspections required 

by paragraph (h)(1) of this AD. 

(i) For airplanes with line numbers 1 

through 1231 inclusive: Install a cross beam 

repair and preventative modification of the 

outboard radius of the lower corners (forward 

and aft) of the door frame, in accordance with 

Boeing Service Bulletin 737–52–1100, 

Revision 2, dated March 31, 1994. 

(ii) For airplanes with line numbers 1232 

and subsequent: Install a cross beam repair 

and preventative modification of the 

outboard radius of the lower corners (forward 

and aft) of the door frame, in accordance with 

a method approved by the Manager, Seattle 

ACO, or in accordance with data meeting the 

type certification basis of the airplane 

approved by the Boeing Commercial 

Airplanes ODA that has been authorized by 

the Manager, Seattle ACO, to make those 

findings. 

(i) Retained Terminating Action 

This paragraph restates the requirements of 

paragraph (c) of AD 2000–07–06, 

Amendment 39–11660 (65 FR 19302, April 

11, 2000), with revised service information. 

Within 4 years or 12,000 flight cycles after 

May 16, 2000 (the effective date of AD 2000– 

07–06), whichever occurs later: Install the 

preventative modification of the outboard 

radius of the lower corners (forward and aft) 

of the door frame and the reinforcement 

modification of the cross beam of the forward 

cargo door, in accordance with paragraph 

(i)(1) or (i)(2) of this AD, as applicable. 

Accomplishment of paragraph (i)(1) or (i)(2) 

of this AD, as applicable, constitutes 

terminating action for the repetitive 

inspections required by paragraphs (g)(1) and 

(h)(1) of this AD. 

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Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 31393 

(1) For airplanes with line numbers 1 

through 1231 inclusive: Accomplish the 

preventative modification and the 

reinforcement modification, in accordance 

with Boeing Service Bulletin 737–52–1100, 

Revision 2, dated March 31, 1994. 

(2) For airplanes with line numbers 1232 

and subsequent: Accomplish the preventative 

modification and the reinforcement 

modification, in accordance with a method 

approved by the Manager, Seattle ACO, or in 

accordance with data meeting the type 

certification basis of the airplane approved 

by the Boeing Commercial Airplanes ODA 

that has been authorized by the Manager, 

Seattle ACO, to make those findings; or in 

accordance with Boeing Alert Service 

Bulletin 737–52A1100, Revision 5, dated 

February 14, 2011. As of the effective date of 

this AD, use only Boeing Alert Service 

Bulletin 737–52A1100, Revision 5, dated 

February 14, 2011, to accomplish the 

modifications required by this paragraph. 

(j) Retained Action for Airplanes on Which 

Modifications Were Accomplished 

Previously 

This paragraph restates the requirements of 

paragraph (d) of AD 2000–07–06, 

Amendment 39–11660 (65 FR 19302, April 

11, 2000). For all airplanes on which 

modifications of the forward lower corner of 

the door frame and the cross beam of the 

forward cargo door were accomplished as 

specified in Boeing Service Bulletin 737–52– 

1100, dated August 25, 1988, or Revision 1, 

dated July 20, 1989; or in accordance with 

the requirements of AD 90–06–02, 

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

1990): Within 4 years or 12,000 flight cycles 

after May 16, 2000 (the effective date of AD 

2000–07–06), whichever occurs later, install 

the reinforcement modification of the aft 

corner of the door frame of the forward cargo 

door, in accordance with Boeing Service 

Bulletin 737–52–1100, Revision 2, dated 

March 31, 1994. Accomplishment of such 

modification constitutes terminating action 

for the repetitive inspections required by 

paragraphs (g)(1) and (h)(1) of this AD. 

(k) New Inspections and Corrective Actions 

Except as provided by paragraphs (m)(1) 

and (m)(2) of this AD: At the applicable time 

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

Boeing Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011, do the 

inspections required by paragraphs (k)(1) and 

(k)(2) of this AD, as applicable. Do all 

applicable related investigative and 

corrective actions before further flight, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–52A1100, Revision 5, dated February 14, 

2011; except as required by paragraph (m)(3) 

of this AD. Accomplishment of the 

inspections required by paragraph (k) of this 

AD terminates the requirements of the 

repetitive inspections required by paragraphs 

(g)(1) and (h)(1) of this AD. If any cracking 

is found in the number 4 cross beam, before 

further flight, repair in accordance with 

Boeing Special Attention Service Bulletin 

737–52–1149, dated December 11, 2003. 

Note 2 to paragraph (k) of this AD: Boeing 

Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011, refers to 

Boeing Special Attention Service Bulletin 

737–52–1149, dated December 11, 2003, as 

an additional source of guidance for the 

inspection for cracks of the number 4 cross 

beam. 

(1) For airplanes identified in Tables 1 and 

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

Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011: Do a 

one-time HFEC inspection of the applicable 

location for cracks, in accordance with the 

Work Instructions, Part I, of Boeing Alert 

Service Bulletin 737–52A1100, Revision 5, 

dated February 14, 2011. 

(2) For airplanes identified in Table 3 of 

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

Service Bulletin 737–52A1100, Revision 5, 

dated February 14, 2011: Do a one-time 

general visual inspection of the 

reinforcement angle for excessive shimming 

or fastener pull-up, in accordance with the 

Work Instructions, Part III, of Boeing Alert 

Service Bulletin 737–52A1100, Revision 5, 

dated February 14, 2011. 

(l) No Supplemental Structural Inspections 

Required by This AD 

(1) The supplemental structural 

inspections specified in Table 4 of paragraph 

1.E., ‘‘Compliance,’’ and Part 5 of the 

Accomplishment Instructions, of Boeing 

Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011, are not 

required by this AD. 

(2) The supplemental structural 

inspections specified in Table 4 of paragraph 

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

Bulletin 737–52A1100, Revision 5, dated 

February 14, 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 of Boeing Alert Service Bulletin 

737–52A1100, Revision 5, dated February 14, 

2011, are not required by this AD. 

(m) Exceptions to Certain Service 

Information 

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

Boeing Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011, 

specifies a compliance time relative to the 

Revision 5 issue date of that service bulletin, 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Where Table 1, ‘‘Condition’’ column of 

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

Alert Service Bulletin 737–52A1100, 

Revision 5, dated February 14, 2011, 

specifies ‘‘airplanes without either the repair 

or modification accomplished in accordance 

with previous releases of this service 

bulletin,’’ the corresponding condition in this 

AD is for ‘‘airplanes on which either a repair 

or modification was not accomplished before 

the effective date of this AD.’’ 

(3) Where Boeing Alert Service Bulletin 

737–52A1100, Revision 5, dated February 14, 

2011, specifies to contact Boeing for certain 

actions: Before further flight, do the repair 

using a method approved in accordance with 

the procedures specified in paragraph (n)(1) 

of this AD. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, 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 2000–07–06, 

Amendment 39–11660 (65 FR 19302, April 

11, 2000), are approved as AMOCs for the 

corresponding requirements of this AD. 

(o) Related Information 

(1) 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. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

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

5680; Internet https:// 

www.myboeingfleet.com. You may review 

copies of the referenced service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, Washington. 

For information on the availability of this 

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

(p) 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 June 28, 2013. 

(i) Procedure 4, ‘‘Surface Inspection of 

Aluminum Parts (Meter Display),’’ of Section 

51–00–00, of Part 6, ‘‘Eddy Current,’’ of 

Boeing 737 Nondestructive Test (NDT) 

Manual, D6–37239, Revision 108, dated 

November 15, 2012. The revision level of this 

document is identified only in the letter of 

transmittal; no other page of this document 

contains this information. 

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31394 Federal Register / Vol. 78, No. 101 / Friday, May 24, 2013 / Rules and Regulations 

(ii) Procedure 23, ‘‘Aluminum Part Surface 

Inspection (Impedance Plane Display),’’ 

Section 51–00–00, of Part 6, ‘‘Eddy Current,’’ 

of Boeing 737 Nondestructive Test (NDT) 

Manual, D6–37239, Revision 108, dated 

November 15, 2012. The revision level of this 

document is identified only in the letter of 

transmittal; no other page of this document 

contains this information. 

(iii) Boeing Alert Service Bulletin 737– 

52A1100, Revision 5, dated February 14, 

2011. 

(iv) Boeing Special Attention Service 

Bulletin 737–52–1149, dated December 11, 

2003. 

(4) The following service information was 

approved for IBR on May 16, 2000 (65 FR 

19302, April 11, 2000). 

(i) Figure 4, of Section 51–00–00, of Part 

6, of Boeing 737 Nondestructive Test (NDT) 

Manual, D6–37239, dated August 5, 1997. 

The revision level is not specified on the title 

page or list of effective pages of this 

document. The title page of this document is 

not dated. Pages 1 and 2 of the list of 

effective pages of this document are dated 

August 5, 1997; page 2A is dated February 5, 

1997. 

(ii) Figure 23, of Section 51–00–00, of Part 

6, of Boeing 737 Nondestructive Test (NDT) 

Manual, D6–37239, dated August 5, 1997. 

The revision level is not specified on the title 

page or list of effective pages of this 

document. The title page of this document is 

not dated. Pages 1 and 2 of the list of 

effective pages of this document are dated 

August 5, 1997; page 2A is dated February 5, 

1997. 

(iii) Boeing Service Bulletin 737–52–1100, 

Revision 2, dated March 31, 1994. 

(5) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P. O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

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

5680; Internet https:// 

www.myboeingfleet.com. 

(6) You may view this service information 

at FAA, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356. 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/ibr-locations.html. 

Issued in Renton, Washington, on April 26, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–10797 Filed 5–23–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0445; Directorate 

Identifier 2012–SW–098–AD; Amendment 

39–17458; AD 2013–10–05] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

Deutschland GmbH Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Deutschland GmbH (ECD) 

Model MBB–BK 117 C–2 helicopters. 

This AD requires revising the operating 

limitations to prohibit flights under 

instrument flight rules (IFR) or under 

night visual flight rules (VFR) when the 

autotrim is inoperative. The actions of 

this AD are intended to prevent a 

workload situation whereby stabilizing 

the helicopter in flight would be 

difficult if not impossible, resulting in 

possible loss of helicopter control. 

DATES: This AD becomes effective June 

10, 2013. 

We must receive comments on this 

AD by July 23, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov or in person at the 

Docket Operations Office between 9 

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

Friday, except Federal holidays. The AD 

docket contains this AD, the economic 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http:// 

www.eurocopter.com/techpub. 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. 

FOR FURTHER INFORMATION CONTACT: 

George Schwab, Aviation Safety 

Engineer, Safety Management Group, 

Rotorcraft Directorate, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

george.schwab@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, we invite you to participate in 

this rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit them only one time. We will file 

in the docket all comments that we 

receive, as well as a report summarizing 

each substantive public contact with 

FAA personnel concerning this 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, issued EASA AD No. 2012–0216, 

dated October 18, 2012, to correct an 

unsafe condition for ECD Model MBB– 

BK 117 C–2 helicopters. EASA advises 

that the autopilot (AP) of a Model MBB– 

BK 117 C–2 helicopter failed in flight 

with ‘‘ACTUATOR’’ and ‘‘BACKUP 

SAS’’ messages appearing on the 

caution and advisory display, ‘‘AP’’ 

illuminated in red on the warning unit, 

and Y (Yaw actuator) and P (pitch 

actuator) on the primary flight display. 

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