23468 Federal Register / Vol. 78, No. 76 / Friday, April 19, 2013 / Rules and Regulations 

Issued in Renton, Washington, on April 4, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08905 Filed 4–18–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0803; Directorate 

Identifier 2011–NM–214–AD; Amendment 

39–17419; AD 2013–08–02] 

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) 

that applies to all The Boeing Company 

Model 777–200, –200LR, –300, and 

–300ER series airplanes. That AD 

currently requires repetitive inspections 

for cracking of the elevator actuator 

fittings. This new AD requires, for 

previously modified airplanes, 

repetitive inspections for movement of 

the fittings or fastener heads, and 

eventual replacement of certain bolts 

(including related investigative and 

corrective actions if necessary). For all 

airplanes, this replacement, with 

corrected torque values, would 

terminate the requirements of the 

existing AD. This new AD also removes 

certain airplanes from the applicability. 

This AD was prompted by the 

manufacturer’s development of a 

modification that was approved as an 

optional terminating action to the 

existing AD’s required repetitive 

inspections. We have been advised that 

the modification procedures include 

certain incorrect torque values. We are 

issuing this AD to detect and correct a 

cracked actuator fitting or incorrectly 

installed bolts to the actuator fitting, 

which could lead to the elevator 

becoming detached and unrestrained, 

and a consequent unacceptable flutter 

condition and loss of control of the 

airplane. 

DATES: This AD is effective May 24, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of May 24, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of January 22, 2008 (72 FR 

71212, December 17, 2007). 

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; 

fax206–766–5680; 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: 

Melanie Violette, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

985057–3356; phone: 425–917–6422; 

fax: 425–917–6590; email: 

melanie.violette@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2007–26–05, 

Amendment 39–15307 (72 FR 71212, 

December 17, 2007). That AD applies to 

the specified products. The NPRM 

published in the Federal Register on 

August 3, 2012 (77 FR 46340). The 

NPRM proposed to continue to require 

repetitive dye penetrant or highfrequency eddy current (HFEC) 

inspections, or detailed inspections for 

cracking of the elevator actuator fittings, 

and replacement of any cracked fitting. 

The NPRM also proposed to require, for 

previously modified airplanes, 

repetitive inspections for movement of 

the fittings or fastener heads, and 

eventual replacement of certain bolts 

(including related investigative and 

corrective actions if necessary). For all 

airplanes, this replacement, with 

corrected torque values, would 

terminate the requirements of the 

existing AD. The NPRM also proposed 

to remove certain airplanes from the 

applicability. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 46340, 

August 3, 2012) and the FAA’s response 

to each comment. 

Support for the NPRM (77 FR 46340, 

August 3, 2012) 

Boeing supports the NPRM (77 FR 

46340, August 3, 2012). 

Request To Amend Installed Part 

Number (P/N) 

Air New Zealand requested that we 

revise the NPRM (77 FR 46340, August 

3, 2012) to require that the installed part 

number be amended to reflect 

accomplishment of Boeing Alert Service 

Bulletin 777–55A0016, Revision 1, 

dated August 25, 2011, instead of the 

current data plate modification. Air 

New Zealand explained that the benefits 

of Boeing re-numbering the modified 

elevator assembly would be to ensure 

that the airplane shows clear pre/post 

modification configuration of the 

elevator assemblies, and also that the 

part number changes would add clarity. 

Air New Zealand reasoned that, 

otherwise, installing a pre-modified 

elevator and not re-instating the repeat 

inspection per Boeing Alert Service 

Bulletin 777–55A0015 would be an 

unsafe condition and that the airplane 

would be out of compliance with the 

NPRM. 

Air New Zealand also indicated that 

accomplishment of Boeing Alert Service 

Bulletin 777–55A0016, Revision 1, 

dated August 25, 2011, leaves the 

elevator assembly part number 

unaffected, but the elevator data plate 

has the service bulletin added to it. Air 

New Zealand also noted that Boeing 

Alert Service Bulletin 777–55A0016, 

Revision 1, dated August 25, 2011, 

modifies the elevator as a stand-alone 

component and does not affect the 

airframe. Further, Air New Zealand 

stated that the elevator assembly is an 

interchangeable component, but the 

current illustrated parts catalog (IPC) 

does not show a one-way part 

interchangeability with pre- and postembodiment of Boeing Alert Service 

Bulletin 777–55A0016, Revision 1, 

dated August 25, 2011, terminating 

action assemblies due to the part 

number remaining unchanged. 

Air New Zealand expressed that, if an 

operator accomplishes Boeing Alert 


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Service Bulletin 777–55A0016, Revision 

1, dated August 25, 2011, the repeat 

inspections of Boeing Alert Service 

Bulletin 777–55A0015 are terminated. 

Air New Zealand stated that the risk is 

that if an unscheduled maintenance 

occurs that replaces the elevator, the 

operator could potentially install a premodified elevator and not reinstate the 

repeat mandatory inspections specified 

in Boeing Alert Service Bulletin 777– 

55A0015, because no part number 

changed and no IPC interchangeability 

information was available. 

We do not agree to revise this AD to 

require that the installed part number be 

amended instead of the current data 

plate modification. The operator is 

responsible for ensuring that each 

airplane is maintained in an airworthy 

condition, and is in compliance with all 

regulations. FAA Advisory Circular 39– 

9, ‘‘Airworthiness Directives 

Management Process,’’ Change 2, dated 

December 7, 2012 (http://rgl.faa.gov/ 

Regulatory_and_Guidance_Library/ 

rgAdvisoryCircular.nsf/0/ 

31573c7680b14363862578a80051646f/ 

$FILE/AC%2039-9%20CHG%202.pdf), 

describes acceptable means for 

complying with Part 39 requirements for 

ADs. Boeing has amended the elevator 

part number, effective with airplane line 

number 718, which had the modified 

fitting installed in production. The IPC 

currently shows that the new elevator 

(P/N 183W0061–17/18) may not be 

replaced by an older one (e.g., P/N 

183W0061–15/16). 

However, we have discovered the 

existence of a P/N 183W0001 elevator 

interchangeability drawing, internal to 

Boeing, which potentially could permit 

parts covered within the scope of this 

AD to be installed on airplanes beyond 

the scope of this AD. Therefore, we have 

added new paragraph (m) to this AD 

that explicitly prohibits the use of the 

elevator interchangeability drawing 

with this AD, to preclude its use in the 

event that the drawing becomes 

available to operators. 

Request To Allow for Optional 

Replacement 

American Airlines (AA) requested 

that we revise the NPRM (77 FR 46340, 

August 3, 2012) to allow for optional 

replacement of the fittings with new, 

improved fittings using Boeing Alert 

Service Bulletin 777–55A0016, Revision 

1, dated August 25, 2011. 

We agree with the request to allow for 

optional replacement of the fittings with 

new, improved fittings using Boeing 

Alert Service Bulletin 777–55A0016, 

Revision 1, dated August 25, 2011. 

Paragraph (i) of the NPRM (77 FR 46340, 

August 3, 2012) already allows for the 

optional replacement of the fittings with 

new fittings using Boeing Alert Service 

Bulletin 777–55A0016, Revision 1, 

dated August 25, 2011. No change is 

necessary in this regard. 

Request To Exclude Requirement From 

Service Bulletin in NPRM (77 FR 46340, 

August 3, 2012) 

AA requested that we revise the 

NPRM (77 FR 46340, August 3, 2012) to 

state that the instruction to ‘‘Put the 

airplane back to serviceable condition,’’ 

which is found in Boeing Alert Service 

Bulletin 777–55A0016, Revision 1, 

dated August 25, 2011, is not required 

by the NPRM. AA explained that this 

requirement does not affect the 

condition that the NPRM seeks to 

address. AA reasoned that, as most 

operators will accomplish these 

modifications as part of a maintenance 

visit, returning the airplane to a 

serviceable condition will not be 

possible in the context of that statement, 

but would occur instead at a point in 

time well after this work is complete. 

We agree with the request to state that 

the phrase ‘‘Put the airplane back to 

serviceable condition,’’ which is 

referenced in the service information 

specified in this AD, is not mandated by 

this final rule. Other regulations require 

restoring the airplane to serviceable 

condition before further flight. 

Therefore, we added an exception in a 

new paragraph (j)(2) of this AD 

regarding the language in the service 

information. In addition, we added a 

reference to paragraph (j)(2) in 

paragraphs (g)(1), (g)(2), (h), (h)(1)(ii), 

(h)(2) and (i) of this AD. 

Request for Credit for Elevator 

Installation 

United Airlines (UA) requested that 

we revise the NPRM (77 FR 46340, 

August 3, 2012) to include terminating 

action credit for the installation of a 

new elevator, as specified by Boeing 

Alert Service Bulletin 777–55A0016, 

dated October 27, 2009, including the 

correct torque values specified in 

Boeing Alert Service Bulletin 777– 

55A0016, Revision 1, dated August 25, 

2011. UA explained that paragraph (k) 

of the NPRM (paragraph (l) of this final 

rule) does not provide credit for 

installation of a new elevator that has 

complied with the actions specified in 

Boeing Alert Service Bulletin 777– 

55A0016, dated October 27, 2009, 

including the correct torque values 

specified in Boeing Alert Service 

Bulletin 777–55A0016, Revision 1, 

dated August 25, 2011. UA expressed 

that, following accomplishment of 

Boeing Alert Service Bulletin 777– 

55A0016, dated October 27, 2009, using 

the higher torque values, it removed 

both elevators and inspected the 

fasteners using Boeing procedures. UA 

stated that damage was found on the 

right-hand elevator and it elected to 

replace the existing elevator (–2B) with 

a new production elevator (–18B), 

which had the post-service bulletin 

configuration with the new actuator 

fittings installed from production using 

the correct torque values for the 

fasteners. 

We agree to allow replacement of 

elevators, as an additional method of 

compliance for this AD. We have added 

paragraph (k) to this final rule to allow 

replacement. 

Explanation of Change Made to This 

AD 

We have clarified in paragraph (g)(2) 

of this final rule, that after the effective 

date of this AD, Boeing Service Bulletin 

777–55A0015, Revision 3, dated 

November 24, 2009, must be used to 

accomplish the actions required by 

paragraph (g)(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 the AD 

with the changes described previously— 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (77 FR 

46340, August 3, 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 46340, 

August 3, 2012) 

We also determined that these 

changes 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 139 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 


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ESTIMATED COSTS

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

Inspection (retained actions 

from AD 2007–26–05, 

Amendment 39–15307 (72 

FR 71212, December 17, 

2007)).

10 work-hours × $85 per hour 

= $850, per inspection 

cycle.

$0 $850, per inspection cycle ..... $118,150, per inspection 

cycle. 

Inspection (new action) .......... 14 work-hours × $85 per hour 

= $1,190, per inspection 

cycle.

0 $1,190 .................................... Up to $165,410, per inspection cycle. 

We estimate the following costs to do 

any necessary replacements 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 replacements: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Fitting replacement ................................................... 132 work-hours × $85 per hour = $11,220 .............. $21,643 $32,863 

Bolt replacement ....................................................... 105 work-hours × $85 per hour = $8,925 ................ $65 $8,990 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2007–26–05, Amendment 39–15307 (72 

FR 71212, December 17, 2007), and 

adding the following new AD: 

2013–08–02 The Boeing Company: 

Amendment 39–17419; Docket No. 

FAA–2012–0803; Directorate Identifier 

2011–NM–214–AD. 

(a) Effective Date 

This airworthiness directive (AD) is 

effective May 24, 2013. 

(b) Affected ADs 

This AD supersedes AD 2007–26–05, 

Amendment 39–15307 (72 FR 71212, 

December 17, 2007). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200, –200LR, –300, and –300ER 

series airplanes, certificated in any category, 

as identified in Boeing Alert Service Bulletin 

777–55A0016, Revision 1, dated August 25, 

2011. 

(d) Subject 

Joint Aircraft System Component (JASC)/ 

Air Transport Association (ATA) of America 

Code 55, Stabilizers. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

cracked left elevator actuator fitting, and the 

recent determination that certain incorrect 

torque values had been specified for an 

alternative method of compliance intended to 

terminate the requirements of AD 2007–26– 

05, Amendment 39–15307 (72 FR 71212, 

December 17, 2007). We are issuing this AD 

to detect and correct a cracked actuator 

fitting or incorrectly installed bolts to the 

actuator fitting, which could lead to the 

elevator becoming detached and 

unrestrained, and a consequent unacceptable 

flutter condition and loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspections and Corrective 

Actions With Revised Service Information 

This paragraph restates the inspections and 

corrective actions required by paragraph (f) of 

AD 2007–26–05, Amendment 39–15307 (72 

FR 71212, December 17, 2007), with revised 

service information. 

(1) Except as provided by paragraph (j)(2) 

of this AD: Do all inspections and actions 

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

this AD, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–55A0015, dated April 

19, 2007; or Boeing Service Bulletin 777– 

55A0015, Revision 3, dated November 24, 

2009. At the applicable time specified in 

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

Alert Service Bulletin 777–55A0015, dated 


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April 19, 2007, except as provided by 

paragraph (g)(3) of this AD, do an initial dye 

penetrant or high frequency eddy current 

(HFEC) inspection for cracking of the elevator 

actuator fittings, and, thereafter, do repetitive 

dye penetrant, HFEC, or detailed inspections 

at the applicable times specified in paragraph 

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

Bulletin 777–55A0015, dated April 19, 2007. 

As of the effective date of this AD, Boeing 

Service Bulletin 777–55A0015, Revision 3, 

dated November 24, 2009, must be used to 

accomplish the actions required by this 

paragraph. 

(2) Before further flight, replace any fitting 

found to be cracked during any inspection 

required by paragraph (g)(1) of this AD with 

a new fitting having the same part number, 

or an optional part number, as identified in 

Boeing Alert Service Bulletin 777–55A0015, 

dated April 19, 2007; or Boeing Service 

Bulletin 777–55A0015, Revision 3, dated 

November 24, 2009; except as provided by 

paragraph (j)(2) of this AD. Thereafter, do 

initial and repetitive inspections of the 

replacement fitting at the time specified in 

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

Alert Service Bulletin 777–55A0015, dated 

April 19, 2007. As of the effective date of this 

AD, Boeing Service Bulletin 777–55A0015, 

Revision 3, dated November 24, 2009, must 

be used to accomplish the actions required 

by this paragraph. 

(3) Where Boeing Alert Service Bulletin 

777–55A0015, dated April 19, 2007, specifies 

a compliance time after the date on that 

service bulletin, this AD requires compliance 

within the specified compliance time after 

January 22, 2008 (the effective date of AD 

2007–26–05, Amendment 39–15307 (72 FR 

71212, December 17, 2007)). 

(h) New Additional Actions for Certain 

Airplanes 

For airplanes on which the elevator 

actuator fitting assemblies have been 

replaced using the fastener torque values 

specified in Boeing Alert Service Bulletin 

777–55A0016, dated October 27, 2009: 

Within 180 days after the effective date of 

this AD, do a detailed inspection of the 

elevator actuator fitting assemblies to detect 

discrepancies (including indications of 

fastener head movement and fitting 

movement along the spar web), in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 777–55A0016, 

Revision 1, dated August 25, 2011, except as 

provided by paragraph (j)(2) of this AD. 

(1) If no discrepancy is detected, do the 

actions specified in paragraphs (h)(1)(i) and 

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

(i) Repeat the inspection thereafter at 

intervals not to exceed 90 days or 360 flight 

cycles, whichever occurs first, until the 

actions specified in paragraph (h)(1)(ii) of 

this AD are done. 

(ii) Within 4,200 flight cycles or 750 days 

after the effective date of this AD, whichever 

occurs first, replace the 12 bolts common to 

the elevator actuator fitting and the spar web, 

and do all applicable related investigative 

and corrective actions, in accordance with 

the Accomplishment Instructions of Boeing 

Alert Service Bulletin 777–55A0016, 

Revision 1, dated August 25, 2011, except as 

provided by paragraphs (j)(1) and (j)(2) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

The replacement of all 12 bolts in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 777–55A0016, 

Revision 1, dated August 25, 2011, 

terminates the requirements of paragraphs (g) 

and (h) of this AD for that fitting only. 

(2) If any discrepancy is detected, before 

further flight, replace the 12 bolts common to 

the elevator actuator fitting and the spar web 

using new parts, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–55A0016, Revision 1, dated August 25, 

2011, except as provided by paragraphs (j)(1) 

and (j)(2) of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. The replacement of all 12 bolts 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–55A0016, Revision 1, dated August 25, 

2011, terminates the requirements of 

paragraphs (g) and (h) of this AD for that 

fitting only. 

(i) New Optional Replacement of Elevator 

Actuator Fitting Assembly 

For airplanes on which the elevator 

actuator fitting assemblies have not been 

replaced as specified in Boeing Alert Service 

Bulletin 777–55A0016, dated October 27, 

2009: Replacement of these fitting assemblies 

with new parts, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–55A0016, Revision 1, 

dated August 25, 2011, except as provided by 

paragraphs (j)(1) and (j)(2) of this AD, 

terminates the requirements of paragraphs (g) 

and (h) of this AD. 

(j) Exceptions 

(1) If any discrepancy or cracking is found 

during any inspection required by this AD, 

and Boeing Alert Service Bulletin 777– 

55A0016, Revision 1, dated August 25, 2011, 

specifies to contact Boeing for appropriate 

action: Before further flight, repair using a 

method approved in accordance with the 

procedures specified in paragraph (n) of this 

AD. 

(2) Where the service bulletins identified 

in paragraphs (j)(2)(i), (j)(2)(ii), and (j)(2)(iii) 

of this AD specify to ‘‘Put airplane back in 

a serviceable condition,’’ this AD does not 

require that action. 

(i) Boeing Alert Service Bulletin 777– 

55A0015, dated April 19, 2007. 

(ii) Boeing Service Bulletin 777–55A0015, 

Revision 3, dated November 24, 2009. 

(iii) Boeing Alert Service Bulletin 777– 

55A0016, Revision 1, dated August 25, 2011. 

(k) New Optional Replacement of Elevator 

Replacing the elevator with a new elevator 

terminates the requirements of paragraphs (g) 

and (h) of this AD, provided that the elevator 

actuator fitting configuration on the new 

elevator complies with the modification and 

bolt torque values defined in the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–55A0016, Revision 1, 

dated August 25, 2011. 

(l) Credit for Previous Actions 

This paragraph provides credit for 

inspecting and replacing actuator fittings, as 

required by paragraph (g) of this AD, if the 

inspection and replacement were performed 

before the effective date of this AD using a 

service bulletin specified in paragraph (l)(1) 

or (l)(2) of this AD, and using the correct 

torque values as specified in Boeing Alert 

Service Bulletin 777–55A0016, Revision 1, 

dated August 25, 2011. 

(1) Boeing Service Bulletin 777–55A0015, 

Revision 1, dated January 31, 2008, which is 

not incorporated by reference in this AD. 

(2) Boeing Service Bulletin 777–55A0015, 

Revision 2, dated December 4, 2008, which 

is not incorporated by reference in this AD. 

(m) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may use the interchangeability table 

on Boeing Elevator Assembly Drawing 

183W0001 (Table 1, Sheet 1), to install an 

elevator or elevator part on any airplane. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by The 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved previously in 

accordance with AD 2007–26–05, 

Amendment 39–15307 (72 FR 71212, 

December 17, 2007), are not approved as 

AMOCs for this AD. 

(o) Related Information 

(1) For more information about this AD, 

contact Melanie Violette, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 985057– 

3356; phone: 425–917–6422; fax: 425–917– 

6590; email: melanie.violette@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, WA 98124–2207; telephone 206– 

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

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


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may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington 985057–3356. 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 May 24, 2013. 

(i) Boeing Service Bulletin 777–55A0015, 

Revision 3, dated November 24, 2009. 

(ii) Boeing Alert Service Bulletin 777– 

55A0016, Revision 1, dated August 25, 2011. 

(4) The following service information was 

approved for IBR on January 22, 2008 (72 FR 

71212, December 17, 2007). 

(i) Boeing Alert Service Bulletin 777– 

55A0015, dated April 19, 2007. 

(ii) Reserved. 

(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. 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 April 2, 

2013. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08742 Filed 4–18–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

Bureau of Industry and Security 

15 CFR Part 748 

[Docket No. 130322279–3279–01] 

RIN 0694–AF90 

Amendments to Existing Validated 

End-User Authorizations: CSMC 

Technologies Corporation in the 

People’s Republic of China (PRC) 

AGENCY: Bureau of Industry and 

Security, Commerce. 

ACTION: Final rule. 

SUMMARY: In this rule, the Bureau of 

Industry and Security (BIS) amends the 

Export Administration Regulations 

(EAR) to revise the existing 

Authorization Validated End-User 

(VEU) listing for CSMC Technologies 

Corporation (CSMC) in the People’s 

Republic of China (PRC). Specifically, 

BIS amends Supplement No. 7 to part 

748 of the EAR to update VEU CSMC’s 

current list of ‘‘eligible destinations.’’ 

DATES: This rule is effective April 19, 

2013. 

FOR FURTHER INFORMATION CONTACT: 

Karen Nies-Vogel, Chair, End-User 

Review Committee, Bureau of Industry 

and Security, U.S. Department of 

Commerce, 14th Street & Pennsylvania 

Avenue NW., Washington, DC 20230; by 

telephone: (202) 482–5991, fax: (202) 

482–3991, or email: ERC@bis.doc.gov. 

SUPPLEMENTARY INFORMATION: 

Background 

Authorization Validated End-User 

Validated end-users (VEUs) are 

designated entities located in eligible 

destinations to which eligible items may 

be exported, reexported, or transferred 

(in-country) under a general 

authorization instead of a license. The 

names of the VEUs, as well as the date 

they were so designated, and their 

respective eligible destinations and 

items are identified in Supplement No. 

7 to part 748 of the EAR. Under the 

terms described in that supplement, 

VEUs may obtain eligible items without 

an export license from BIS, in 

conformity with Section 748.15 of the 

EAR. Eligible items vary between VEUs 

but may include commodities, software, 

and technology, except those controlled 

for missile technology or crime control 

reasons. 

VEUs are reviewed and approved by 

the U.S. Government in accordance with 

the provisions of Section 748.15 and 

Supplement Nos. 8 and 9 to part 748 of 

the EAR. The End-User Review 

Committee (ERC), composed of 

representatives from the Departments of 

State, Defense, Energy and Commerce, 

and other agencies, as appropriate, is 

responsible for administering the VEU 

program. BIS amended the EAR in a 

final rule published on June 19, 2007 

(72 FR 33646) to create Authorization 

VEU. 

Amendment to an Existing Validated 

End-User Authorization in the PRC 

Revisions to the List of Eligible 

Destinations and Postal Code for CSMC 

Technologies Corporation 

In this rule, BIS amends Supplement 

No. 7 to part 748 of the EAR to amend 

CSMC’s current list of eligible 

destinations. Specifically, BIS removes 

Wuxi CR Semiconductor Wafers and 

Chips Co., Ltd. from CSMC’s list of 

eligible destinations. BIS is not making 

this change in response to activities of 

concern. Rather, BIS is making this 

change to CSMC’s list of VEU-eligible 

destinations as a result of the merger of 

Wuxi CR Semiconductor Wafers & 

Chips Co., Ltd. and CSMC Technologies 

Fab 1 Co., Ltd., which is also listed as 

one of CSMC’s eligible destinations. In 

addition, BIS amends CSMC’s 

authorization by updating the postal 

code for one of CSMC’s eligible 

destinations. 

Names and Former Addresses of 

Facilities 

Validated End-User: CSMC 

Technologies Corporation. 

Eligible Destinations: 

CSMC Technologies Fab 1 Co., Ltd., 14 

Liangxi Road, Wuxi, Jiangsu 214061, 

China. 

CSMC Technologies Fab 2 Co., Ltd., 8 

Xinzhou Rd., Wuxi National New HiTech Industrial Development Zone, 

Wuxi, Jiangsu 214061, China. 

Wuxi CR Semiconductor, Wafers and 

Chips Co., Ltd., 14 Liangxi Road, 

Wuxi, Jiangsu 214061, China. 

Names and Updated Addresses of 

Facilities 

Validated End-User: CSMC 

Technologies Corporation. 

Eligible Destinations: 

CSMC Technologies Fab 1 Co., Ltd., 14 

Liangxi Road, Wuxi, Jiangsu 214061, 

China. 

CSMC Technologies Fab 2 Co., Ltd., 8 

Xinzhou Road, Wuxi National New 

Hi-Tech Industrial Development 

Zone, Wuxi, Jiangsu 214028, China. 

Since August 21, 2001, the Export 

Administration Act (the Act) has been 

in lapse and the President, through 

Executive Order 13222 of August 17, 

2001 (3 CFR, 2001 Comp., p. 783 

(2002)), as extended most recently by 

the Notice of August 15, 2012, 77 FR 

49699 (August 16, 2012), has continued 

the EAR in effect under the 

International Emergency Economic 

Powers Act. BIS continues to carry out 

the provisions of the Act, as appropriate 

and to the extent permitted by law, 

pursuant to Executive Order 13222. 


emcdonald on DSK67QTVN1PROD with RULES