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

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


## 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


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

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:



### E STIMATED 

### C OSTS

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:



### O N 

### -C ONDITION 

### C OSTS

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:


## 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.


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

(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.


## 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.