Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41101 

(4) 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. 

(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 25, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–15800 Filed 7–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0867; Directorate 

Identifier 2013–NM–115–AD; Amendment 

39–17853; AD 2014–11–03] 

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 777–200, 

–200LR, –300, and –300ER series 

airplanes. This AD was prompted by 

reports of severe corrosion on bonding 

jumpers installed on the flight control 

surfaces. This AD requires repetitive 

bonding jumper inspections for 

corrosion, sealant disbond, and 

insufficient sealant coverage; and 

corrective actions if necessary. This AD 

also specifies an optional inspection for 

corrosion damage of the bonding 

brackets, and corrective actions if 

necessary, which would terminate the 

repetitive inspections. For certain 

airplanes, this AD requires installing 

certain bonding jumpers, and replacing 

single-tabbed brackets with two-tabbed 

brackets. We are issuing this AD to 

detect and correct corrosion on bonding 

jumpers installed on the flight control 

surfaces, which, in the event of a 

lightning strike, could damage the 

actuator control electronics (ACEs) and 

result in the loss of the ability to 

command individual flight control 

surfaces or cause uncommanded motion 

of individual flight control surfaces. 

DATES: This AD is effective August 19, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 19, 2014. 

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. 

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–2013– 

0867; 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: 

Georgios Roussos, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, Seattle Aircraft Certification 

Office, FAA, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6482; fax: 425–917–6590; email: 

Georgios.Roussos@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 777–200, –200LR, –300, and 

–300ER series airplanes. The NPRM 

published in the Federal Register on 

October 25, 2013 (78 FR 63903). The 

NPRM was prompted by reports of 

severe corrosion on bonding jumpers 

installed on the flight control surfaces. 

The NPRM proposed to require 

repetitive bonding jumper inspections 

for corrosion, sealant disbond, and 

insufficient sealant coverage; and 

corrective actions if necessary. The 

NPRM also specified an optional 

inspection for corrosion damage of the 

bonding brackets, and corrective actions 

if necessary, which would terminate the 

repetitive inspections. For certain 

airplanes, the NPRM proposed installing 

certain bonding jumpers, and replacing 

single-tabbed brackets with two-tabbed 

brackets. We are issuing this AD to 

detect and correct corrosion on bonding 

jumpers installed on the flight control 

surfaces, which, in the event of a 

lightning strike, could damage the ACEs 

and result in the loss of the ability to 

command individual flight control 

surfaces or cause uncommanded motion 

of individual flight control surfaces. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 63903, 

October 25, 2013) and the FAA’s 

response to each comment. 

Request To Base Compliance Time on 

AD Issue Date 

American Airlines (AAL) requested 

that paragraph (f) of the proposed AD 

(78 FR 63903, October 25, 2013) be 

revised to allow operators to comply 

with Boeing Service Bulletin 777– 

27A0078, Revision 1, dated April 1, 

2013, within 36 months after the AD 

effective date. AAL stated that Boeing 

Alert Service Bulletin 777–27A0078, 

dated September 10, 2009, was issued 

with a compliance time of 36 months 

from the original release of the service 

bulletin. AAL explained that after 

Boeing Alert Service Bulletin 777– 

27A0078, dated September 10, 2009, 

was released, Boeing accomplished a 

service bulletin validation on another 

operator’s airplane and found many 

discrepancies and errors with the work 

instructions and parts required, 

resulting in Revision 1 of Boeing Service 

Bulletin 777–27A0078, dated April 1, 

2013. AAL stated that due to the issues 

still existing in the work instructions for 

Boeing Alert Service Bulletin 777– 

27A0078, dated September 10, 2009, 

and a long lead time on the part kits, 

operators will be unable to accomplish 

Boeing Service Bulletin 777–27A0078, 

Revision 1, dated April 1, 2013, by the 

compliance time given without severe 

disruption of schedules. 

We agree with the commenter’s 

request. We agree that the compliance 

time should be based on the effective 

date of this final rule and not on the 

original issue date of Boeing Service 

Bulletin 777–27A0078, Revision 1, 

dated April 1, 2013. We had already 

included this information in the 

proposed AD (78 FR 63903, October 25, 

2013), paragraph (j)(1) of this AD, as 


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41102 Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 

reiterated from the proposed AD, states 

that where Boeing Service Bulletin 777– 

27A0078, Revision 1, dated April 1, 

2013, specifies a compliance time after 

the ‘‘Original issue date of this service 

bulletin,’’ this AD requires compliance 

within the specified compliance time 

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

Therefore, no change is required for this 

AD in this regard. 

Request To Revise Repetitive Inspection 

Interval 

Boeing requested that we revise 

paragraph (g) of the proposed AD (78 FR 

63903, October 25, 2013) to extend the 

compliance time for the repetitive 

inspections from 48 months to 1,500 

days in order to allow operators to do 

these inspections at the same time as 

other inspections which are on a 1,500- 

day cycle mandated by the Model 777 

airplane maintenance planning 

document. Boeing stated that current 

guidance on developing a compliance 

recommendation requires that airline 

maintenance inspection intervals (AMII) 

be taken into account when determining 

the compliance time. Boeing explained 

that for the Model 777 series airplanes, 

these AMII are given in calendar days 

and cycles, and that deviation from the 

AMII requires justification. Boeing 

stated that since no such justification 

exists, if the compliance time were to be 

determined today, it would be 1,500 

days (4 maintenance years) instead of 48 

months (4 calendar years). 

We agree with the commenter’s 

request. The requested change to the 

repetitive inspection interval meets the 

compliance time that has been 

determined for addressing the identified 

unsafe condition, while taking into 

account fleet-established maintenance 

intervals. We have revised paragraph (g) 

of this AD to specify a repetitive 

inspection interval of 1,500 days. 

Request to Clarify Inspection Method 

United Airlines (UAL) requested that 

we revise paragraph (g) of the proposed 

AD (78 FR 63903, October 25, 2013), 

which specifies to do a detailed 

inspection using a borescope if the 

horizontal stabilizer tips have not been 

removed. UAL requested that we clarify 

the required action by including ‘‘as 

applicable’’ or by noting that this 

borescope inspection applies only to 

bonding jumper number 10. 

We infer that the commenter refers to 

the work instructions in Boeing Service 

Bulletin 777–27A0078, Revision 1, 

dated April 1, 2013, that identify the 

option of using a borescope to inspect 

bonding jumper 10 if the horizontal 

stabilizer tips have not been removed. 

We agree with the commenter’s request. 

The use of a borescope is intended for 

bonding jumper 10, and not for all 

bonding jumpers. We have revised 

paragraph (g) of this AD to specify doing 

the detailed inspection using a 

borescope if the horizontal stabilizer 

tips have not been removed. 

Revisions Made to This Final Rule 

We have revised the Costs of 

Compliance in this final rule to specify 

only the mandated actions, since we 

have no definitive data for the oncondition costs. We have also revised 

the concurrent cost estimates by 

including the estimated number of 

airplanes on which those actions must 

be accomplished. 

We have revised paragraph (h)(1) of 

this AD to clarify that the optional 

terminating action for Option 2 includes 

replacing bonding jumpers. 

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 (78 FR 

63903, October 25, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 63903, 

October 25, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 131 

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 bonding jumpers 

(131 airplanes) .......................

Up to 67 work-hours × $85 

per hour = Up to $5,695 

per inspection cycle.

$0 Up to $5,695 per inspection 

cycle.

Up to $746,045 per inspection 

cycle. 

Concurrent action; Boeing 

Service Bulletin 

777-55A0010, Revision 1, 

dated April 17, 2001.

(34 airplanes) .........................

66 work-hours × $85 per hour 

= $5,610.

2,668 $8,278 .................................... $281,452. 

Concurrent action; Boeing 

Service Bulletin 

777-55A0014, Revision 1, 

dated April 1, 2010.

(84 airplanes) .........................

21 work-hours × $85 per hour 

= $1,785.

1,235 $3,020 .................................... $253,680. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

and optional terminating 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. 


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Federal Register / Vol. 79, No. 135 / Tuesday, July 15, 2014 / Rules and Regulations 41103 

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. 

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): 

2014–11–03 The Boeing Company: 

Amendment 39–17853; Docket No. 

FAA–2013–0867; Directorate Identifier 

2013–NM–115–AD. 

(a) Effective Date 

This AD is effective August 19, 2014. 

(b) Affected ADs 

This AD affects AD 2012–08–13, 

Amendment 39–17030 (77 FR 24357, April 

24, 2012). 

(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 Service Bulletin 777– 

27A0078, Revision 1, dated April 1, 2013. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by reports of severe 

corrosion on bonding jumpers installed on 

the flight control surfaces. We are issuing this 

AD to detect and correct corrosion on 

bonding jumpers installed on the flight 

control surfaces, which, in the event of a 

lightning strike, could damage the actuator 

control electronics (ACEs) and result in the 

loss of the ability to command individual 

flight control surfaces or cause 

uncommanded motion of individual flight 

control surfaces. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Bonding Jumper or Bracket Inspection 

At the applicable compliance time 

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

Boeing Service Bulletin 777–27A0078, 

Revision 1, dated April 1, 2013, except as 

specified in paragraphs (j)(1) and (j)(2) of this 

AD: Do a general visual inspection or a 

detailed inspection, including a borescopic 

inspection as applicable, for corrosion, 

sealant disbond, and insufficient sealant 

coverage of bonding jumpers; and do all 

applicable corrective actions; in accordance 

with Option 1, and Option 2, as applicable, 

of the Accomplishment Instructions of 

Boeing Service Bulletin 777–27A0078, 

Revision 1, dated April 1, 2013, except as 

required by paragraph (j)(3) of this AD. Do a 

detailed inspection using a borescope of 

bonding jumper 10 if the horizontal stabilizer 

tips have not been removed. Do all applicable 

corrective actions before further flight. 

Repeat the inspection thereafter at intervals 

not to exceed 1,500 days. Doing the actions 

specified in paragraph (h)(1) of this AD on a 

bonding jumper terminates the repetitive 

inspections required by this paragraph. Doing 

the actions specified in paragraph (h)(2) of 

this AD terminates repetitive inspections 

required by this paragraph for that bonding 

jumper. 

(h) Optional Terminating Actions 

(1) Doing a general visual inspection or a 

detailed inspection for corrosion damage of 

the bonding jumper brackets, replacing 

bonding jumpers, and all applicable 

corrective actions; in accordance with Option 

2 of the Accomplishment Instructions of 

Boeing Service Bulletin 777–27A0078, 

Revision 1, dated April 1, 2013; terminates 

the repetitive inspections required by 

paragraph (g) of this AD. Do all applicable 

corrective actions before further flight. 

(2) The repetitive inspections required by 

paragraph (g) of this AD are not required on 

the bonding jumpers that were removed, 

inspected, and replaced with new bonding 

jumpers and new fasteners using the new 

category 2 fay sealed direct standard ground 

stud installation method, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 777–27A0078, Revision 1, 

dated April 1, 2013. 

(i) Prior and Concurrent Requirements 

(1) For Group 1 airplanes, as identified in 

Boeing Service Bulletin 777–27A0078, 

Revision 1, dated April 1, 2013: Prior to or 

concurrently with accomplishing the actions 

required by paragraph (g) of this AD, install 

new bonding jumpers, and do resistance 

measurements of the modified installation to 

verify resistance is within the limits specified 

in the Accomplishment Instructions of 

Boeing Service Bulletin 777–55A0010, 

Revision 1, dated April 17, 2001. Do the 

actions in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 777–55A0010, Revision 1, 

dated April 17, 2001. 

Note 1 to paragraph (i)(1) of this AD: AD 

2012–08–13, Amendment 39–17030 (77 FR 

24357, April 24, 2012), refers to Boeing 

Service Bulletin 777–55A0010, Revision 1, 

dated April 17, 2001, as the appropriate 

source of service information for 

accomplishing the actions specified in 

paragraph (h) of AD 2012–08–13. 

(2) For Group 1 and Group 2 airplanes, as 

identified in Boeing Service Bulletin 777– 

27A0078, Revision 1, dated April 1, 2013: 

Prior to or concurrently with accomplishing 

the actions required by paragraph (g) of this 

AD, replace certain single-tabbed bonding 

brackets in the airplane empennage with twotabbed bonding brackets, in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin 777–55A0014, Revision 1, 

dated April 1, 2010. 

Note 2 to paragraph (i)(2) of this AD: AD 

2012–08–13, Amendment 39–17030 (77 FR 

24357, April 24, 2012), refers to Boeing 

Service Bulletin 777–55A0014, Revision 1, 

dated April 1, 2010, as the appropriate source 

of service information for accomplishing the 

actions specified in paragraph (g) of AD 

2012–08–13. 

(j) Exceptions to Service Information 

(1) Where Boeing Service Bulletin 777– 

27A0078, Revision 1, dated April 1, 2013, 

specifies a compliance time after the 

‘‘Original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) The ‘‘Condition’’ column in paragraph 

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

Bulletin 777–27A0078, Revision 1, dated 

April 1, 2013, refers to a condition as of the 

‘‘Original Issue date of this service bulletin.’’ 

This AD applies to the corresponding 

condition as of the effective date of this AD. 

(3) If any corrosion damage is found during 

any inspection required by this AD, and 

Boeing Service Bulletin 777–27A0078, 

Revision 1, dated April 1, 2013, specifies to 

contact Boeing for appropriate action: Before 

further flight, repair the corrosion damage 

using a method approved in accordance with 

the procedures specified in paragraph (l) of 

this AD. 

(k) Credit for Previous Actions 

(1) For Groups 1, 2, and 6 through 9, as 

identified in Boeing Alert Service Bulletin 

777–27A0078, dated September 10, 2009: 

This paragraph provides credit for actions 

required by paragraph (g) of this AD and the 

actions specified in paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 


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Service Bulletin 777–27A0078, dated 

September 10, 2009, which is not 

incorporated by reference in this AD. 

(2) For Groups 3 through 5, as identified 

in Boeing Alert Service Bulletin 777– 

27A0078, dated September 10, 2009: This 

paragraph provides credit for actions 

required by paragraph (g) of this AD, except 

for the actions required for bonding jumpers 

21 and 22, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 777–27A0078, 

dated September 10, 2009, which is not 

incorporated by reference in this AD. If a 

review of the airplane’s maintenance records 

positively determines that bonding jumpers 

21 and 22 were inspected before the effective 

date of this AD in accordance with Option 1 

of Work Package 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–27A0078, dated September 10, 2009, 

this paragraph provides credit for the actions 

required by paragraph (g) of this AD for the 

inspected bonding jumpers. 

(3) For Groups 3 through 5, as identified 

in Boeing Alert Service Bulletin 777– 

27A0078, dated September 10, 2009: This 

paragraph provides credit for actions 

specified in paragraph (h) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Alert Service 

Bulletin 777–27A0078, dated September 10, 

2009, which is not incorporated by reference 

in this AD; provided that a review of the 

airplane’s maintenance records positively 

determines that bonding jumpers 21 and 22 

were replaced in accordance with Option 2 

of Work Package 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–27A0078, dated September 10, 2009, or 

were replaced using the new Category 2 fay 

sealed direct ground stud installation 

method. 

(4) This paragraph provides credit for 

actions required by paragraph (i)(1) of this 

AD if those actions were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin 777–55A0010, dated 

October 26, 2000, which is not incorporated 

by reference in this AD. 

(5) This paragraph provides credit for 

actions required by paragraph (i)(2) of this 

AD if those actions were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin 777–55A0014, dated 

May 8, 2008, which is not incorporated by 

reference in 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 

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

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your Principal Maintenance Inspector 

or Principal Avionics Inspector, as 

appropriate, or lacking a principal inspector, 

your local Flight Standards 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 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 

(1) For more information about this AD, 

contact Georgios Roussos, Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, Seattle Aircraft Certification 

Office, FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6482; fax: 

425–917–6590; email: Georgios.Roussos@

faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be viewed at the addresses specified in 

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

(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 777–27A0078, 

Revision 1, dated April 1, 2013. 

(ii) Boeing Service Bulletin 777–55A0010, 

Revision 1, dated April 17, 2001. 

(iii) Boeing Service Bulletin 777–55A0014, 

Revision 1, dated April 1, 2010. 

(3) 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. 

(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 May 14, 

2014. 

Michael J. Kaszycki, 

Acting Manager Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–15435 Filed 7–14–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0296; Directorate 

Identifier 2012–NM–102–AD; Amendment 

39–17861; AD 2014–11–10] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2008–08– 

09 for certain Bombardier, Inc. Model 

CL–600–2B19 (Regional Jet Series 100 & 

440) airplanes. AD 2008–08–09 required 

revising the airworthiness limitations 

(AWL) section of the Instructions for 

Continued Airworthiness by 

incorporating procedures for repetitive 

functional tests of the pilot input lever 

of the pitch feel simulator (PFS) units 

and corrective actions if necessary. This 

new AD requires replacing certain PFS 

units with new redesigned PFS units, 

which would terminate the repetitive 

functional tests; and both adding and 

removing certain airplanes from the 

applicability. This AD was prompted by 

reports that the shear pin in the input 

lever of several PFS units failed due to 

fatigue; and by the development of a redesigned PFS unit, which eliminates the 

need for repetitive functional tests. We 

are issuing this AD to prevent 

undetected failure of the shear pins of 

both PFS units simultaneously, which 

could result in loss of pitch feel forces 

and consequent reduced control of the 

airplane. 

DATES: This AD becomes effective 

August 19, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 19, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2013-0296; or in 

person at the 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. 

For service information identified in 

this AD, contact Bombardier, Inc., 400 

Coˆte-Vertu Road West, Dorval, Que ́bec 

H4S 1Y9, Canada; telephone 514–855– 

5000; fax 514–855–7401; email thd.crj@


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