34252 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 

the requirements of paragraph (g) of this AD 

for Model A300–600 airplanes. 

(i) Where the tables in paragraph 1.E.(2), 

‘‘Accomplishment Timescale,’’ of Airbus 

Service Bulletin A300–57–6029, Revision 08, 

dated April 25, 2013, specify a grace period 

for doing the actions for airplanes that have 

exceeded the thresholds, this AD requires, for 

all airplanes, that the actions be done within 

the specified grace period after the effective 

date of this AD or before the specified 

thresholds, whichever occurs later. 

(ii) Where Airbus Service Bulletin A300– 

57–6029, Revision 08, dated April 25, 2013, 

specifies to ‘‘contact Airbus’’ before further 

flight, this AD requires repairing using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or European 

Aviation Safety Agency (EASA); or Airbus’s 

EASA Design Organization Approval (DOA); 

and accomplishing those actions before 

further flight. If approved by the DOA, the 

approval must include the DOA-authorized 

signature. 

(2) If, during any inspection as required by 

paragraph (h)(1) of this AD, discrepancies are 

detected, before next flight, accomplish the 

applicable corrective actions, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A300–57–6029, 

Revision 08, dated April 25, 2013. 

(3) Corrective actions, as required by 

paragraph (h)(2) of this AD, do not constitute 

terminating action for the repetitive 

inspection requirements of paragraph (h)(1) 

of this AD. 

(i) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g) of this AD, 

if those actions were performed before April 

23, 2008 (the effective date of AD 2008–06– 

18, Amendment 39–15430 (73 FR 14670, 

March 19, 2008)), using the applicable 

service information identified in paragraphs 

(i)(1)(i) through (i)(1)(iv) of this AD, which 

are not incorporated by reference by this AD. 

(i) Airbus Service Bulletin A300–57–0177, 

Revision 03, dated May 29, 2006 (for Model 

A300 series airplanes). 

(ii) Airbus Service Bulletin A300–57–0177, 

Revision 04, dated January 5, 2007 (for Model 

A300 series airplanes). 

(iii) Airbus Service Bulletin A300–57– 

6029, Revision 04, dated May 29, 2006 (for 

Model A300–600 series airplanes). 

(iv) Airbus Service Bulletin A300–57– 

6029, Revision 05, dated October 23, 2006 

(for Model A300–600 series airplanes). 

(2) This paragraph provides credit for 

actions required by paragraph (g) or (h) of 

this AD, if those actions were performed 

before the effective date of this AD, using 

Airbus Service Bulletin A300–57–6029, 

Revision 07, dated June 6, 2011 (for Model 

A300–600 series airplanes), which is not 

incorporated by reference by this AD. 

(j) 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: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–2125; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. 

(i) 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. 

(ii) AMOCs approved previously for AD 

2008–06–18, Amendment 39–15430 (73 FR 

14670, March 19, 2008), are approved as 

AMOCs for the corresponding requirements 

of this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the EASA; or Airbus’s EASA DOA. If 

approved by the DOA, the approval must 

include the DOA-authorized signature. 

(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. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0203, dated 

October 1, 2012, for related information. This 

MCAI may be found in the AD docket on the 

Internet at http://www.regulations.gov by 

searching for and locating Docket No. FAA– 

2014–0618. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (l)(5) and (l)(6) of this AD. 

(l) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on July 21, 2015. 

(i) Airbus Service Bulletin A300–57–6029, 

Revision 08, dated April 25, 2013. 

(ii) Reserved. 

(4) The following service information was 

approved for IBR on April 23, 2008 (73 FR 

14670, March 19, 2008). 

(i) Airbus Service Bulletin A300–57–0177, 

Revision 05, dated March 23, 2007. 

(ii) Airbus Service Bulletin A300–57–6029, 

Revision 06, dated March 23, 2007. 

(5) For service information identified in 

this AD, contact Airbus SAS Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(6) You may view this 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 June 3, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–14283 Filed 6–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0485; Directorate 

Identifier 2014–NM–093–AD; Amendment 

39–18176; AD 2015–12–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2007–13– 

05 for all The Boeing Company Model 

777–200, –200LR, –300, and –300ER 

series airplanes. AD 2007–13–05 

required repetitive measurements of the 

freeplay of the right and left elevators, 

rudder, and rudder tab, and related 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 34253 

investigative and corrective actions if 

necessary. This new AD requires 

repetitive freeplay inspections and 

lubrication of the right and left 

elevators, rudder, and rudder tab, and 

related investigative and corrective 

actions if necessary. This AD was 

prompted by the manufacturer’s 

determination that the procedure for the 

rudder freeplay inspection does not 

properly detect excessive freeplay in the 

rudder control load loop. We are issuing 

this AD to detect and correct excessive 

wear in the load loop components of the 

control surfaces, which could lead to 

excessive freeplay of the control 

surfaces, flutter, and consequent loss of 

control of the airplane. 

DATES: This AD is effective July 21, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of July 21, 2015. 

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 view 

this 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. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0485. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0485; 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 

Docket 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: 

Haytham Alaidy, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6573; 

fax: 425–917–6590; email: 

Haytham.Alaidy@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2007–13–05, 

Amendment 39–15109 (72 FR 33856, 

June 20, 2007). AD 2007–13–05 applied 

to all The Boeing Company Model 777– 

200, –200LR, –300, and –300ER series 

airplanes. The NPRM published in the 

Federal Register on July 29, 2014 (79 FR 

43981). The NPRM was prompted by a 

determination by the manufacturer that, 

after AD 2007–13–05 was issued, the 

procedure for the rudder freeplay 

inspection did not properly detect 

excessive freeplay in the rudder control 

load loop. The NPRM proposed to 

continue to require repetitive freeplay 

inspections and lubrication of the right 

and left elevators, rudder, and rudder 

tab; and related investigative and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

excessive wear in the load loop 

components of the control surfaces, 

which could lead to excessive freeplay 

of the control surfaces, flutter, and 

consequent loss of control of the 

airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 43981, 

July 29, 2014) and the FAA’s response 

to each comment. 

A4A, on behalf of American Airlines 

(AA), stated that AA is already in 

compliance with the requirements 

proposed in the NPRM (79 FR 43981, 

July 29, 2014). 

Request To Exclude Certain Airplanes 

Boeing requested that the airplanes 

referenced in the SUMMARY section and 

Discussion paragraph of the NPRM (79 

FR 43981, July 29, 2014) be changed 

from ‘‘all The Boeing Company Model 

777 airplanes’’ to ‘‘most of The Boeing 

Company Model 777 airplanes.’’ Boeing 

stated that Model 777–200F airplanes 

are not affected by the NPRM. 

We agree to change the phrase ‘‘all 

The Boeing Company Model 777 

airplanes’’ for clarity. This final rule 

supersedes AD 2007–13–05, 

Amendment 39–15109 (72 FR 33856, 

June 20, 2007), which was applicable to 

all Boeing Model 777–200, –200LR, 

–300, and –300ER series airplanes. At 

the time AD 2007–13–05 was published, 

all Model 777–200, –200LR, –300, and 

–300ER series airplanes were referred to 

as ‘‘all The Boeing Company Model 777 

airplanes.’’ Since then, Model 777F has 

been added to the U.S. type certificate 

data sheet. We have revised the 

SUMMARY section of this final rule to 

specify all The Boeing Company Model 

777–200, –200LR, –300, and –300ER 

series airplanes. The Discussion 

paragraph of the NPRM (79 FR 43981, 

July 29, 2014) is not restated in this final 

rule. 

Request To Clarify the Unsafe 

Condition 

Boeing requested that we clarify the 

unsafe condition specified in the 

SUMMARY section, Discussion paragraph, 

and paragraph (e) of the NPRM. Boeing 

stated that the repetitive freeplay 

inspections of the right and left 

elevators, rudder, and rudder tab 

proposed in the NPRM (79 FR 43981, 

July 29, 2014) would not prevent, 

detect, or correct flutter; the proposed 

freeplay inspections would detect 

excessive wear in the load loop 

components of the control surfaces. 

Boeing pointed out that excessive wear 

could lead to excessive freeplay of the 

control surfaces, which could cause 

unacceptable airframe vibration during 

flight. 

Based on the explanation provided by 

the commenter, we agree to clarify the 

unsafe condition that is the basis for 

issuing this final rule. However, we will 

not replace the word ‘‘flutter’’ with 

‘‘unacceptable airframe vibration’’ 

because the unsafe condition is flutter, 

not vibration. We have revised the 

unsafe condition statement as follows, 

‘‘We are issuing this AD to detect and 

correct excessive wear in the load loop 

components of the control surfaces, 

which could lead to excessive freeplay 

of the control surfaces, flutter, and 

consequent loss of control of the 

airplane.’’ This revision appears in the 

SUMMARY section and Discussion 

paragraph of the SUPPLEMENTARY

INFORMATION section of this final rule, as 

well as paragraph (e) of this AD. 

Request To Clarify the Requirements of 

Paragraph (g) of the Proposed AD (79 

FR 43981, July 29, 2014) 

Boeing requested that we revise 

paragraph (g) of the proposed AD (79 FR 

43981, July 29, 2014) by deleting 

‘‘rudder’’ from the following sentence: 

‘‘If during any inspection required by 

this paragraph, the rudder freeplay 

exceeds any applicable measurement 

. . . .’’ Boeing explained that this 

statement is incorrect because it is not 

just the rudder freeplay, but if any 

elevator, rudder, or rudder tab freeplay 

exceeds any applicable measurement 

specified in the service information, the 


asabaliauskas on DSK5VPTVN1PROD with RULES
34254 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 

applicable corrective actions need to be 

accomplished before further flight. 

We agree to revise the specified 

sentence in paragraph (g) of this AD, 

because corrective actions before further 

flight are needed for any elevator, 

rudder, or rudder tab freeplay that 

exceeds any applicable measurement 

specified in Boeing Special Attention 

Service Bulletin 777–27–0062, Revision 

2, dated January 27, 2014. 

Requests To Correct Errors in the 

Service Information 

Japan Airlines (JAL) and United 

Airlines noted that there are 

typographical errors in Appendix B and 

Appendix C of Boeing Special Attention 

Service Bulletin 777–27–0062, Revision 

2, dated January 27, 2014. JAL requested 

that the FAA issue an AD to mandate 

the incorporation of the next revision 

(Revision 3) of Boeing Special Attention 

Service Bulletin 777–27–0062, or 

provide an exception to these 

typographical errors in this AD. United 

Airlines requested that the FAA issue a 

global alternative method of compliance 

(AMOC) to correct the errors identified 

in Boeing Special Attention Service 

Bulletin 777–27–0062, Revision 2, dated 

January 27, 2014. 

We agree that Appendix B and 

Appendix C of Boeing Special Attention 

Service Bulletin 777–27–0062, Revision 

2, dated January 27, 2014, contain 

typographical errors. However, we do 

not consider that delaying this action 

until after the release of the 

manufacturer’s planned service bulletin 

revision is warranted. Because some of 

these typographical errors affect the 

procedures for correctly measuring the 

freeplay of the rudder tab surface, we 

have provided the corrections for those 

errors in paragraph (i) of this AD instead 

of issuing an AMOC. Paragraph (i) of the 

proposed AD (79 FR 43981, July 29, 

2014) has been redesignated as 

paragraph (i)(1) in this AD, and new 

paragraphs (i)(2), (i)(3), and (i)(4) have 

been added to this AD. We have also 

revised paragraph (g) of this AD to refer 

to paragraphs (i)(1) through (i)(4) of this 

AD. 

Additional Changes to This Final Rule 

Paragraph (k)(4) of the NPRM (79 FR 

43981, July 29, 2014) stated that AMOCs 

approved previously for AD 2007–13– 

05, Amendment 39–15109 (72 FR 

33856, June 20, 2007), are not approved 

as AMOCS for the requirements of this 

AD. We have now determined that 

AMOCs for certain actions required by 

AD 2007–13–05 are acceptable for the 

corresponding requirements of this AD. 

We have revised paragraph (k)(4) of this 

AD and added new paragraphs (k)(5) 

and (k)(6) to this AD to include this 

information. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously, 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

43981, July 29, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 43981, 

July 29, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Special 

Attention Service Bulletin 777–27– 

0062, Revision 2, dated January 27, 

2014. The service information describes 

procedures for repetitive freeplay 

inspections and lubrication of the right 

and left elevators, rudder, and rudder 

tab, and related investigative and 

corrective actions. This service 

information is reasonably available 

because the interested parties have 

access to it through their normal course 

of business or by the means identified 

in the ADDRESSES section of this AD. 

Costs of Compliance 

We estimate that this AD affects 142 

airplanes of U.S. registry. The new 

actions of this AD would add no 

additional economic burden to that 

imposed by AD 2007–13–05, 

Amendment 39–15109 (72 FR 33856, 

June 20, 2007). The current costs for this 

AD are repeated for the convenience of 

affected operators, as follows: 

ESTIMATED COSTS

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

Measurement (inspection), elevator.4 work-hours × $85 per hour 

= $340 per measurement 

(inspection) cycle.

$0 $340 per measurement (inspection) cycle.$48,280 per measurement 

(inspection) cycle. 

Lubrication, elevator ............... 17 work-hours × $85 per hour 

= $1,445 per lubrication 

cycle.

0 $1,445 per lubrication cycle ... $205,190 per lubrication 

cycle. 

Measurement (inspection), 

rudder.

4 work-hours × $85 per hour 

= $340 per measurement 

(inspection) cycle.

0 $340 per measurement (inspection) cycle.$48,280 per measurement 

(inspection) cycle. 

Lubrication, rudder ................. 7 work-hours × $85 per hour 

= $595 per lubrication cycle.

0 $595 per lubrication cycle ...... $84,490 per lubrication cycle. 

Measurement (inspection), 

rudder tab.

3 work-hours × $85 per hour 

= $255 per measurement 

(inspection) cycle.

0 $255 per measurement (inspection) cycle.$36,210 per measurement 

(inspection) cycle. 

Lubrication, rudder tab ........... 5 work-hours × $85 per hour 

= $425 per lubrication cycle.

0 $425 per lubrication cycle ...... $60,350 per lubrication cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition corrective 

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 


asabaliauskas on DSK5VPTVN1PROD with RULES
Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 34255 

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) 

2007–13–05, Amendment 39–15109 (72 

FR 33856, June 20, 2007), and adding 

the following new AD: 

2015–12–03 The Boeing Company: 

Amendment 39–18176 ; Docket No. 

FAA–2014–0485; Directorate Identifier 

2014–NM–093–AD. 

(a) Effective Date 

This AD is effective July 21, 2015. 

(b) Affected ADs 

This AD replaces AD 2007–13–05, 

Amendment 39–15109 (72 FR 33856, June 

20, 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 paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Airplanes having a Variable Number 

identified in paragraph 1.A., ‘‘Effectivity,’’ of 

Boeing Special Attention Service Bulletin 

777–27–0062, Revision 2, dated January 27, 

2014. 

(2) Airplanes having a date of issuance of 

the original airworthiness certificate or date 

of issuance of the original export certificate 

of airworthiness on or after January 27, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by the 

manufacturer’s determination that the 

procedure for the rudder freeplay inspection 

does not properly detect excessive freeplay in 

the rudder control load loop. We are issuing 

this AD to detect and correct excessive wear 

in the load loop components of the control 

surfaces, which could lead to excessive 

freeplay of the control surfaces, flutter, and 

consequent loss of control of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections of Elevators, 

Rudder, and Rudder Tab 

At the applicable times specified in tables 

1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Special Attention Service Bulletin 

777–27–0062, Revision 2, dated January 27, 

2014, except as provided by paragraph (i)(1) 

of this AD: Inspect the freeplay of the right 

and left elevators, rudder, and rudder tab by 

accomplishing all of the actions specified in 

Parts 1, 3, and 5 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–27–0062, Revision 2, 

dated January 27, 2014, except as provided 

by paragraphs (i)(2) through (i)(4) of this AD. 

Repeat the inspections thereafter at the 

intervals specified in tables 1, 2, and 3 of 

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

Special Attention Service Bulletin 777–27– 

0062, Revision 2, dated January 27, 2014. If, 

during any inspection required by this 

paragraph, the freeplay exceeds any 

applicable measurement specified in Part 1, 

3, and 5, as applicable, of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–27– 

0062, Revision 2, dated January 27, 2014, 

before further flight, do the applicable 

corrective actions in accordance with Part 1, 

3, and 5 of the Accomplishment Instructions 

of Boeing Special Attention Service Bulletin 

777–27–0062, Revision 2, dated January 27, 

2014. 

(h) Repetitive Lubrication 

At the applicable times specified in tables 

1, 2, and 3 of paragraph 1.E., ‘‘Compliance,’’ 

of Boeing Special Attention Service Bulletin 

777–27–0062, Revision 2, dated January 27, 

2014, except as provided by paragraph (i)(1) 

of this AD: Lubricate the elevator 

components, rudder components, and rudder 

tab components, by accomplishing all of the 

actions specified in Parts 2, 4, and 6 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–27– 

0062, Revision 2, dated January 27, 2014, as 

applicable. Repeat the lubrication thereafter 

at the interval specified in tables 1, 2, and 3 

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

Special Attention Service Bulletin 777–27– 

0062, Revision 2, dated January 27, 2014, as 

applicable. 

(i) Exception to Service Information 

Specifications 

(1) Where Boeing Special Attention Service 

Bulletin 777–27–0062, Revision 2, dated 

January 27, 2014, specifies a compliance time 

‘‘after the original issue date on this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time after 

July 25, 2007 (the effective date of AD 2007– 

13–05, Amendment 39–15109 (72 FR 33856, 

June 20, 2007)). 

(2) Where Appendix B, paragraph 1.f., 

‘‘Freeplay Inspection,’’ step (8), of Boeing 

Special Attention Service Bulletin 777–27– 

0062, Revision 2, dated January 27, 2014, 

specifies that the center of the pad must be 

within 1.0 inch (13 millimeters) of the center 

line of the rib rivets in the rudder tab, this 

AD requires that the center of the tab must 

be within 1.0 inch (25 millimeters) of the 

center line of the rib rivets in the rudder tab. 

(3) Where Appendix C, paragraph 1.e., 

‘‘Rudder Tab Surface Freeplay—Inspection,’’ 

step (2) and step (6), of Boeing Special 

Attention Service Bulletin 777–27–0062, 

Revision 2, dated January 27, 2014, specify 

that the placement of the force gage and pad 

should be within one inch of the centerline 

line of the middle rudder PCU rib and at 12 

+/¥1 inch (305 +/¥72 millimeters) forward 

of the rudder tab trailing edge, this AD 

requires placement of the force gage and pad 

within one inch of the centerline line of the 

middle rudder PCU rib and at 12 +/¥1 inch 

(305 +/¥25 millimeters) forward of the 

rudder tab trailing edge. 

(4) Where Appendix C, paragraph 1.e., 

‘‘Rudder Tab Surface Freeplay—Inspection,’’ 

step (3), of Boeing Special Attention Service 

Bulletin 777–27–0062, Revision 2, dated 

January 27, 2014, specifies to apply a 30 +/ 

¥pound (133 +/¥14 newton) force, this AD 

requires applying a 30 +/¥3 pound force 

(133 +/¥14 newton) force. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

service information specified in paragraph 

(j)(1) or (j)(2) of this AD. 

(1) Boeing Special Attention Service 

Bulletin 777–27–0062, dated July 18, 2006, 

which was incorporated by reference in AD 

2007–13–05, Amendment 39–15109 (72 FR 

33856, June 20, 2007). 


asabaliauskas on DSK5VPTVN1PROD with RULES
34256 Federal Register / Vol. 80, No. 115 / Tuesday, June 16, 2015 / Rules and Regulations 

(2) Boeing Special Attention Service 

Bulletin 777–27–0062, Revision 1, dated 

October 1, 2009, which is not incorporated 

by reference in this AD. 

(k) 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 

paragraph (l)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@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 for the 

freeplay measurements of the right and left 

elevators and rudder tab required by 

paragraph (f) of AD 2007–13–05, Amendment 

39–15109 (72 FR 33856, June 20, 2007), are 

approved as AMOCs for the corresponding 

requirements of this AD. 

(5) AMOCs approved previously for the 

freeplay measurements of the rudder 

required by paragraph (f) of AD 2007–13–05, 

Amendment 39–15109 (72 FR 33856, June 

20, 2007), are not approved as AMOCs for the 

corresponding requirements of this AD. We 

are not aware of any such AMOCs. 

(6) AMOCs approved previously for the 

repetitive lubrications required by paragraph 

(g) of AD 2007–13–05, Amendment 39–15109 

(72 FR 33856, June 20, 2007), are approved 

as AMOCs for the corresponding 

requirements of this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Haytham Alaidy, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6573; fax: 425– 

917–6590; email: Haytham.Alaidy@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (m)(3) and (m)(4) of this AD. 

(m) 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 Special Attention Service 

Bulletin 777–27–0062, Revision 2, dated 

January 27, 2014. 

(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, WA. 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. 

Issued in Renton, Washington, on June 3, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–14174 Filed 6–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2191; Directorate 

Identifier 2015–CE–019–AD; Amendment 

39–18183; AD 2015–10–51] 

RIN 2120–AA64 

Airworthiness Directives; Avidyne 

Corporation Integrated Flight Displays 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Avidyne Corporation (Avidyne) 

Integrated Flight Displays (IFDs) part 

number (P/N) 700–00083–() loaded with 

software release 9.3.1.0 or earlier release 

(referred to as Model R9—10 inch), P/ 

N 700–00171–() loaded with software 

release 9.2.5.0 or earlier release (referred 

to as Model R9—12 inch), and P/N 700– 

00182–() loaded with software release 

10.0.3.0 or earlier release (referred to as 

Model IFD540). This emergency AD was 

sent previously to all known U.S. 

owners and operators of all aircraft that 

incorporate the above referenced 

Avidyne IFDs. This AD requires 

incorporating an operational limitation 

into the Limitations section of the 

airplane flight manual (AFM) or 

airplane flight manual supplement 

(AFMS). This AD was prompted by 

reports of Avidyne IFDs displaying 

incorrect course deviation indication 

information during GPS approaches 

(incorrect display of lateral deviations). 

We are issuing this AD to correct the 

unsafe condition on these products. 

DATES: This AD is effective July 1, 2015 

to all persons except those persons to 

whom it was made immediately 

effective by Emergency AD 2015–10–51, 

issued on May 18, 2015, which 

contained the requirements of this 

amendment. 

We must receive comments on this 

AD by July 31, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above 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 by searching for 

and locating Docket No. FAA–2015– 

2191; 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 regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (phone: 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Anthony Pigott, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, 12 New England Executive Park, 

Burlington, MA 01803; phone: (781) 

238–7158; fax: (781) 238–7199; email: 

anthony.pigott@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On May 18, 2015, we issued 

Emergency AD 2015–10–51, which 

requires incorporating an operational 

limitation into the Limitations section of 


asabaliauskas on DSK5VPTVN1PROD with RULES