Federal Register / Vol. 78, No. 76 / Friday, April 19, 2013 / Rules and Regulations 23465 

dated July 13, 2012, for your model 

helicopter. 

(v) Before installing a MGB, modify, 

reidentify, and reinstall the chip collector in 

accordance with paragraph (f)(1)(iv) of this 

AD. 

(2) Within 25 hours TIS, and thereafter at 

intervals not exceeding 25 hours TIS: 

(i) For Model AS332C, L, and L1 

helicopters with non-electrical chip detectors 

and electrical chip detectors without a 

caution light on the instrument panel, 

inspect the IGB, TGB, tapered housing, and 

MGB bottom casing chip detectors for a chip 

or metallic particle. 

(ii) For Model AS332L2 helicopters with 

non-electrical chip detectors and electrical 

chip detectors without a caution light on the 

instrument panel, inspect the module, main 

rotor mast tapered housing, IGB, and TGB 

chip detectors for a chip or metallic particle. 

(3) Within 50 hours TIS, and thereafter at 

intervals not exceeding 50 hours TIS: 

(i) For Model AS332C, L, and L1 

helicopters with electrical chip detectors 

with a caution light on the instrument panel, 

inspect the MGB bottom casing, TGB, and 

IGB chip detectors for a chip or metallic 

particle. 

(ii) For Model AS332L2 helicopters with 

electrical chip detectors with a caution light 

on the instrument panel, inspect the MGB 

bottom casing chip detector for a chip or 

magnetic particle. 

(iii) For Model EC225LP helicopters, 

inspect the MGB, IGB, and TGB chip 

detectors for a chip or magnetic particle. If 

there is a chip or magnetic particle, 

determine whether the ‘‘CHIP’’ caution light 

illuminates on the ‘‘Vehicle’’ page of the 

Vehicle Management System. If the ‘‘CHIP’’ 

caution light does not illuminate on the 

‘‘Vehicle’’ page, perform a fault analysis. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Rao Edupuganti, 

Aerospace Engineer, FAA, Rotorcraft 

Directorate, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5110; fax: (817) 

222–5961, email rao.edupaganti@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

(1) Eurocopter Alert Service Bulletin (ASB) 

No. AS332–05–00–94, Revision 0, dated July 

13, 2012, and ASB No. EC225–05A29, 

Revision 0, dated July 13, 2012, which are 

not incorporated by reference, contain 

additional information about the subject of 

this AD. For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, Grand 

Prairie, Texas 75052, telephone (972) 641– 

0000 or (800) 232–0323, fax (972) 641–3775, 

or at http://www.eurocopter.com/techpub. 

You may review a copy of the service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency AD No. 

2012–0129–E, dated July 13, 2012. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6320: Main Rotor Gearbox and 6520: 

Tail Rotor Gearbox. 

(j) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Eurocopter Emergency Alert Service 

Bulletin (EASB) No. 05.00.81, Revision 3, 

dated July 13, 2012. 

Note 1 to paragraph (j)(2)(i): Eurocopter 

EASB No. 05.00.81, Revision 3, dated July 13, 

2012, and EASB No. 05.00.58, Revision 3, 

dated July 13, 2012, were published together 

as a single document. EASB No. 05.00.58, 

Revision 3, dated July 13, 2012 is not 

incorporated by reference. 

(ii) Eurocopter EASB No. 05A017, Revision 

3, dated July 13, 2012. 

Note 2 to paragraph (j)(2)(ii): Eurocopter 

EASB No. 05A017, Revision 3, dated July 13, 

2012, and EASB No. 05A016, Revision 3, 

dated July 13, 2012, were published together 

as a single document. EASB No. 05A016, 

Revision 3, dated July 13, 2012 is not 

incorporated by reference. 

(3) For Eurocopter service information 

identified in this AD, contact American 

Eurocopter Corporation, 2701 N. Forum 

Drive, Grand Prairie, Texas 75052, telephone 

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

641–3775, or at http://www.eurocopter.com/ 

techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) 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 Fort Worth, Texas, on March 27, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–08459 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–2012–0938; Directorate 

Identifier 2011–NM–271–AD; Amendment 

39–17425; AD 2013–08–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–600 

series airplanes. This AD was prompted 

by reports of early fatigue cracks at 

chem-mill areas on the crown skin 

panels. This AD requires repetitive 

inspections for cracking of the fuselage 

skin at certain locations at chem-mill 

areas, and repair if necessary. We are 

issuing this AD to detect and correct 

fatigue cracking of the skin panel at the 

specified chem-mill step locations, 

which could result in rapid 

decompression of the airplane. 

DATES: This AD is effective May 24, 

2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of May 24, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https:// 

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. 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 


emcdonald on DSK67QTVN1PROD with RULES
23466 Federal Register / Vol. 78, No. 76 / Friday, April 19, 2013 / Rules and Regulations 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6447; 

fax: (425) 917–6590; email: 

Wayne.Lockett@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on September 18, 2012 (77 FR 

57541). That NPRM proposed to require 

repetitive inspections for cracking of the 

fuselage skin at certain locations at 

chem-mill areas, and repair 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 57541, 

September 18, 2012) and the FAA’s 

response to each comment. 

Request To Revise Federal Aviation 

Regulations Citations 

Boeing stated that references to 

section 129.109(c)(2) of the Federal 

Aviation regulations (14 CFR 

129.109(c)(2)) are incorrect, since that 

paragraph does not exist in the current 

revision of the Federal Aviation 

Regulations and that the correct 

paragraph reference is section 

129.109(b)(2). Boeing noted that this 

error occurred in the second paragraph 

of the ‘‘Differences Between the 

Proposed AD and the Service 

Information’’ section, and in Note 1 to 

paragraph (k) of the proposed AD (77 FR 

57541, September 18, 2012). 

We agree that the specified references 

are incorrect. We agree that the citation 

in the proposed AD (77 FR 57541, 

September 18, 2012) is inaccurate, but 

since that section of the preamble does 

not reappear in this AD, no 

corresponding change to this AD is 

necessary. We have corrected the 

citation in Note 1 to paragraph (k) of 

this AD. 

Winglet Supplemental Type Certificate 

(STC) Comment 

Aviation Partners Boeing stated that 

the installation of winglets per STC 

ST00830SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/ 

rgstc.nsf/0/408E012E008616A78

62578880060456C?OpenDocument&

Highlight=st00830se) does not affect the 

actions specified in the NPRM (77 FR 

57541, September 18, 2012). 

We concur. We have added paragraph 

(c)(2) to this AD to state that installation 

of STC ST00830SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/408E012E008616A78625

78880060456C?OpenDocument

&Highlight=st00830se) does not affect 

the ability to accomplish the actions 

required by this AD. Therefore, for 

airplanes on which STC ST00830SE 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. 

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 

57541, September 18, 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 57541, 

September 18, 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 6 

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 

Inspection of chem-mill step 

locations.

37 work-hours × $85 per hour 

= $3,145, per inspection 

cycle.

None ........... $3,145, per inspection cycle .. $18,870, per inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

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 

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. 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 76 / Friday, April 19, 2013 / Rules and Regulations 23467 

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 adding 

the following new airworthiness 

directive (AD): 

2013–08–08 The Boeing Company: 

Amendment 39–17425 ; Docket No. 

FAA–2012–0938; Directorate Identifier 

2011–NM–271–AD. 

(a) Effective Date 

This AD is effective May 24, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) This AD applies to The Boeing 

Company Model 737–600 series airplanes, 

certificated in any category, as identified in 

Boeing Service Bulletin 737–53–1309, dated 

October 20, 2011. 

(2) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http:// 

rgl.faa.gov/Regulatory_and_Guidance

_Library/rgstc.nsf/0/408E012E008616A

7862578880060456C?

OpenDocument&Highlight=st00830se) does 

not affect the ability to accomplish the 

actions required by this AD. Therefore, for 

airplanes on which STC ST00830SE 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 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of early 

fatigue cracks at chem-mill areas on the 

crown skin panels. We are issuing this AD to 

detect and correct fatigue cracking of the skin 

panel at the specified chem-mill step 

locations, which could result in rapid 

decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections 

At the applicable time specified in 

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

Service Bulletin 737–53–1309, dated October 

20, 2011, except as required by paragraph (j) 

of this AD: Do an external detailed inspection 

and an external nondestructive inspection (a 

medium frequency eddy current (MFEC), 

magneto optic imager (MOI), C-scan, or 

ultrasonic phased array (UTPA) inspection) 

for cracking in the fuselage skin along the 

chem-mill steps at certain locations specified 

in, and in accordance with, the 

Accomplishment Instructions of Boeing 

Service Bulletin 737–53–1309, dated October 

20, 2011. Repeat the inspections thereafter at 

the applicable times specified in paragraph 

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

Bulletin 737–53–1309, dated October 20, 

2011. 

(h) Repair 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair the cracking 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. Accomplishing the repair approved 

in accordance with the procedures specified 

in paragraph (l) of this AD terminates the 

repetitive inspection requirement for that 

area under the repair only. 

(i) Optional Terminating Modification 

Modification of an inspection area, 

including an external detailed inspection and 

an external nondestructive inspection 

(MFEC, MOI, C-scan, or UTPA) for cracking 

of the area to be modified and a high 

frequency eddy current inspection of all 

existing holes for cracking, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 737–53–1309, dated 

October 20, 2011, terminates the repetitive 

inspections required by paragraph (g) of this 

AD for that modified area only. If any 

cracking is found during any inspection 

described by this paragraph, before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (l) of this AD. 

(j) Service Bulletin Exception 

Boeing Service Bulletin 737–53–1309, 

dated October 20, 2011, specifies compliance 

times ‘‘after the original issue date of this 

service bulletin.’’ However, this AD requires 

compliance within the specified compliance 

times ‘‘after the effective date of this AD.’’ 

(k) Post-Modification Inspections 

The post-modification inspections 

specified in Tables 2 and 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1309, dated October 20, 2011, are not 

required by this AD. 

Note 1 to paragraph (k) of this AD: The 

damage tolerance inspections specified in 

Tables 2 and 3 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

737–53–1309, dated October 20, 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 

actions specified in Part 5 of the 

Accomplishment Instructions and 

corresponding figures of Boeing Service 

Bulletin 737–53–1309, dated October 20, 

2011, are not required by this AD. 

(l) 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. 

(m) Related Information 

For more information about this AD, 

contact Wayne Lockett, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6447; fax: (425) 917–6590; 

email: Wayne.Lockett@faa.gov. 

(n) 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. 

(i) Boeing Service Bulletin 737–53–1309, 

dated October 20, 2011. 

(ii) Reserved. 

(3) 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. 

(4) You may view this service information 

at 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. 

(5) 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. 


emcdonald on DSK67QTVN1PROD with RULES
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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