Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 44669 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplanes identified 

in paragraphs (c)(1), (c)(2), and (c)(3) of this 

AD, certificated in any category. 

(1) Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, serial numbers 10002 through 

10342 inclusive. 

(2) Bombardier, Inc. Model CL–600–2D15 

(Regional Jet Series 705), and Model CL–600– 

2D24 (Regional Jet Series 900) airplanes, 

serial numbers 15001 through 15337 

inclusive. 

(3) Bombardier, Inc. Model CL–600–2E25 

(Regional Jet Series 1000) airplanes, serial 

numbers 19001 through 19040 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by two in-service 

reports of fracture of the rudder pedal tubes 

installed on the pilot-side rudder bar 

assembly. We are issuing this AD to detect 

and correct cracked and damaged pilot-side 

rudder pedal tubes, which could result in 

loss of function of the pilot’s rudder pedal 

during flight, takeoff, or landing, and could 

result in reduced controllability of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections 

Before the accumulation of 26,000 total 

flight cycles or within 3 months after the 

effective date of this AD, whichever occurs 

later: Perform a detailed or eddy current 

inspection for cracking around the aft tapered 

holes of both pilot-side rudder pedal tubes, 

and for damage of the rudder pedal tubes in 

locations other than around the aft tapered 

holes, in accordance with Part A of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–065, including 

Appendix A, dated November 15, 2013. 

Repeat the inspection thereafter at the 

applicable intervals specified in paragraph 

(g)(1) or (g)(2) of this AD, until the 

terminating action specified in paragraph (i) 

of this AD is done. 

(1) If the most recent inspection was a 

detailed inspection: Within 750 flight cycles 

after doing the detailed inspection. 

(2) If the most recent inspection was an 

eddy current inspection: Within 1,250 flight 

cycles after doing the eddy current 

inspection. 

(h) Corrective Actions 

(1) If any crack is found around the aft 

tapered holes during any inspection required 

by paragraph (g) of this AD, before further 

flight, replace the rudder bar assembly, in 

accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–065, including 

Appendix A, dated November 15, 2013. 

(2) If any damage is found during any 

inspection required by paragraph (g) of this 

AD in a location other than around the aft 

tapered holes: Before further flight, repair 

using a method approved by the Manager, 

New York ACO, ANE–170, Engine and 

Propeller Directorate, FAA; or Transport 

Canada Civil Aviation (TCCA); or 

Bombardier, Inc.’s TCCA Design Approval 

Organization (DAO). If approved by the DAO, 

the approval must include the DAOauthorized signature. 

(i) Optional Terminating Action 

Replacement of both pilot-side rudder bar 

assemblies, in accordance with Part B of the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–065, including 

Appendix A, dated November 15, 2013, 

constitutes terminating action for the 

repetitive inspections required by paragraph 

(g) of this AD. 

(j) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. Send information to ATTN: 

Program Manager, Continuing Operational 

Safety, FAA, New York ACO, 1600 Stewart 

Avenue, Suite 410, Westbury, NY 11590; 

telephone 516–228–7300; fax 516–794–5531. 

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. 

(2) Contacting the Manufacturer: 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, New York ACO, ANE–170, 

Engine and Propeller Directorate, FAA; or 

TCCA; or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(k) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2014–02, dated 

January 8, 2014, for related information. This 

MCAI may be found in the AD docket on the 

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

#!documentDetail;D=FAA-2014-0196-0002. 

(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. 

(i) Bombardier Service Bulletin 670BA–27– 

065, including Appendix A, dated November 

15, 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(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 July 17, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17467 Filed 7–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0254; Directorate 

Identifier 2013–NM–047–AD; Amendment 

39–17910; AD 2014–15–08] 

RIN 2120–AA64 

Airworthiness Directives; Beechcraft 

Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Beechcraft Corporation (Type Certificate 

Previously Held by Hawker Beechcraft 

Corporation; Raytheon Aircraft 

Company) Model Hawker 800XP, 

850XP, and 900XP airplanes. This AD 

was prompted by a design review that 

revealed there were no instructions to 

apply sealant to structural components 

in the fuel tank during the winglet 

installation process. This AD requires 

an inspection for the presence of sealant 

on doubler plate edges, doubler plate 

rivets, and adjacent skin in the fuel vent 

surge tanks; and corrective actions if 

necessary. We are issuing this AD to 

detect and correct missing sealant, 

which, during a lightning strike, could 

result in a potential source of ignition in 

a fuel tank and consequent explosion or 


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44670 Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 

fire and subsequent in-flight breakup of 

the airplane. 

DATES: This AD is effective September 5, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 5, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Beechcraft 

Corporation, TMDC, P.O. Box 85, 

Wichita, KS 67201–0085; telephone 

316–676–8238; fax 316–671–2540; email 

tmdc@beechcraft.com; Internet http://

pubs.beechcraft.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–2014– 

0254; 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: 

Jeffrey Englert, Aerospace Engineer, 

Mechanical Systems and Propulsion 

Branch, ACE–116W, FAA, Wichita 

Aircraft Certification Office, 1801 

Airport Road, Room 100, Mid-Continent 

Airport, Wichita, KS 67209; phone: 

316–946–4167; fax: 316–946–4107; 

email: jeffrey.englert@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 Beechcraft Corporation 

(Type Certificate Previously Held by 

Hawker Beechcraft Corporation; 

Raytheon Aircraft Company) Model 

Hawker 800XP, 850XP, and 900XP 

airplanes. The NPRM published in the 

Federal Register on April 24, 2014 (79 

FR 22783). The NPRM was prompted by 

a design review that revealed there were 

no instructions to apply sealant to 

structural components in the fuel tank 

during the winglet installation process. 

The sealant is part of the lightning 

protection design for the fuel tanks. The 

NPRM proposed to require an 

inspection for the presence of sealant on 

doubler plate edges, doubler plate 

rivets, and adjacent skin in the fuel vent 

surge tanks; and corrective actions if 

necessary. We are issuing this AD to 

detect and correct missing sealant, 

which, during a lightning strike, could 

result in a potential source of ignition in 

a fuel tank and consequent explosion or 

fire and subsequent in-flight breakup of 

the airplane. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 22783, April 24, 2014) or on the 

determination of the cost to the public. 

Conclusion 

We reviewed the relevant data and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 

22783, April 24, 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 22783, 

April 24, 2014). 

Costs of Compliance 

We estimate that this AD affects 50 

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 ....................................... 2 work-hours × $85 per hour = 

$170.

None ............................................... $170 $8,500 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per 

product 

Sealant application ....................................................... 36 work-hours × $85 per hour = $3,060 ...................... $32 $3,092 

According to the manufacturer, all of 

the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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 


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Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 44671 

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. 

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): 

2014–15–08 Beechcraft Corporation (Type 

Certificate Previously Held by Hawker 

Beechcraft Corporation; Raytheon 

Aircraft Company): Amendment 39– 

17910; Docket No. FAA–2014–0254; 

Directorate Identifier 2013–NM–047–AD. 

(a) Effective Date 

This AD is effective September 5, 2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Beechcraft Corporation 

(Type Certificate previously held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company) Model Hawker 800XP, 850XP, and 

900XP airplanes, certificated in any category, 

all serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 28, Fuel. 

(e) Unsafe Condition 

This AD was prompted by a design review 

that revealed there were no instructions to 

apply sealant to structural components in the 

fuel tank during the winglet installation 

process. We are issuing this AD to detect and 

correct missing sealant, which, during a 

lightning strike, could result in a potential 

source of ignition in a fuel tank and 

consequent explosion or fire and subsequent 

in-flight breakup of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Action 

For airplanes identified in paragraphs 

(g)(1), (g)(2), and (g)(3) of this AD: Within 600 

flight hours or 12 months after the effective 

date of this AD, whichever occurs first, do a 

general visual inspection for the presence of 

sealant on doubler plate edges, doubler plate 

rivets, and adjacent skin in the top and 

bottom of the left and right fuel vent surge 

tanks, and do all applicable corrective 

actions, in accordance with the 

Accomplishment Instructions of Hawker 

Beechcraft Service Bulletin SB 57–4112, 

dated February 2013, except as required by 

paragraph (i) of this AD. Do all applicable 

corrective actions before further flight. 

(1) Any Beechcraft Corporation (Type 

Certificate previously held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company) Model Hawker 800XP airplane, 

serial numbers 258324, 258326 through 

258332 inclusive, 258334 through 258340 

inclusive, 258342 through 258347 inclusive, 

258349 through 258359 inclusive, 258361 

through 258369 inclusive, 258371 through 

258380 inclusive, 258382 through 258406 

inclusive, 258408 through 258426 inclusive, 

258428 through 258444 inclusive, 258446 

through 258468 inclusive, 258470 through 

258492 inclusive, 258494 through 258512 

inclusive, 258514 through 258532 inclusive, 

258534 through 258540 inclusive, 258542 

through 258555 inclusive, 258557 through 

258566 inclusive, 258278, 258541, 258556, 

258567 through 258609 inclusive, 258611 

through 258628 inclusive, 258630 through 

258684 inclusive, 258686 through 258734 

inclusive, 258736 through 258788 inclusive, 

258795, 258802, 258821, 258825, 258829, 

258834, 258840, and 258847; equipped with 

a kit numbered 140–1701–1, 140–1702–1, 

140–1703–1,140–1703–5, 140–1703–7, or 

140–1704–1 that was purchased from Hawker 

Beechcraft on or before February 13, 2013. 

(2) Any Beechcraft Corporation (Type 

Certificate previously held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company) Model Hawker 850XP airplane 

having serial numbers 258789 through 

258794 inclusive, 258796, 258798 through 

258801 inclusive, 258803 through 258819 

inclusive, 258822, 258823, 258826 through 

258828 inclusive, 258830 through 258833 

inclusive, 258835 through 258838 inclusive, 

258841, 258844, 258845, 258848, 258852, 

258855, 258856, 258858, 258859, 258861, 

258872, 258874, 258876, 258891, 258893, 

258895, 258900, 258901, 258904, 258907, 

258909, 258912, 258915, 258921, 258959, 

258961, 258963, 258977, 258980, 258982, 

and subsequent serial numbers; equipped 

with a kit numbered 140–1701–1, 140–1702– 

1, 140–1703–1, 140–1703–5, 140–1703–7, or 

140–1704–1 that was purchased on or before 

February 13, 2013. 

(3) Beechcraft Corporation (Type 

Certificate previously held by Hawker 

Beechcraft Corporation; Raytheon Aircraft 

Company) Model Hawker 900XP airplanes 

having serial numbers HA–0156 and HA– 

0159. 

(h) Definition 

For the purposes of this AD, a general 

visual inspection is a visual examination of 

an interior or exterior area, installation, or 

assembly to detect obvious damage, failure, 

or irregularity. This level of inspection is 

made from within touching distance unless 

otherwise specified. A mirror may be 

necessary to ensure visual access to all 

surfaces in the inspection area. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or droplight and may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked. 

(i) Exception to the Service Information 

A note in the Accomplishment Instructions 

of the Hawker Beechcraft Service Bulletin SB 

57–4112, dated February 2013, instructs 

operators to contact Hawker Beechcraft if any 

difficulty is encountered in accomplishing 

the service information. However, this AD 

requires that any deviation from the 

instructions provided in Hawker Beechcraft 

Service Bulletin SB 57–4112, dated February 

2013, must be approved as an alternative 

method of compliance (AMOC) under the 

provisions of paragraph (k) of this AD. 

(j) Parts Installation Limitation 

For all airplanes: As of the effective date 

of this AD, no kit having kit number 140– 

1701–1, 140–1702–1, 140–1703–1, 140– 

1703–5, 140–1703–7, or 140–1704–1, that 

was purchased before February 13, 2013, may 

be installed on any airplane unless the 

installation includes sealant on doubler plate 

edges, doubler plate rivets, and adjacent skin 

in the top and bottom of the left and right 

fuel vent surge tanks, as specified in the 

Accomplishment Instructions of Hawker 

Beechcraft Service Bulletin SB 57–4112, 

dated February 2013. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Wichita 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) of this AD. 


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44672 Federal Register / Vol. 79, No. 148 / Friday, August 1, 2014 / Rules and Regulations 

(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. 

(l) Related Information 

For more information about this AD, 

contact Jeffrey Englert, Aerospace Engineer, 

Mechanical Systems and Propulsion Branch, 

ACE–116W, FAA, Wichita Aircraft 

Certification Office, 1801 Airport Road, 

Room 100, Mid-Continent Airport, Wichita, 

KS 67209; phone: 316–946–4167; fax: 316– 

946–4107; email: jeffrey.englert@faa.gov. 

(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) Hawker Beechcraft Service Bulletin SB 

57–4112, dated February 2013. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Beechcraft Corporation, 

TMDC, P.O. Box 85, Wichita, KS 67201– 

0085; telephone 316–676–8238; fax 316–671– 

2540; email tmdc@beechcraft.com; Internet 

http://pubs.beechcraft.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 July 15, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–17325 Filed 7–31–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0145; Directorate 

Identifier 2011–NM–066–AD; Amendment 

39–17899; AD 2014–14–04] 

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) 2003–18– 

10 for certain The Boeing Company 

Model 767 airplanes. AD 2003–18–10 

required revising the Airworthiness 

Limitations Section of the maintenance 

planning data (MPD) document. This 

new AD also requires revising the 

maintenance program to incorporate an 

additional limitation, which terminates 

the existing requirements; and adds 

airplanes to the applicability. This AD 

was prompted by a re-evaluation of 

certain doors and flaps based on their 

fatigue-critical nature. We are issuing 

this AD to detect and correct fatigue 

cracking of the principal structural 

elements (PSEs), which could adversely 

affect the structural integrity of the 

airplane. 

DATES: This AD is effective September 5, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 5, 2014. The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of October 16, 2003 (68 FR 

53503, September 11, 2003). 

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–2012– 

0145; 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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6577; fax: 

425–917–6590; email: berhane.alazar@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2003–18–10, 

Amendment 39–13301 (68 FR 53503, 

September 11, 2003). AD 2003–18–10 

applied to The Boeing Company Model 

767 airplanes. The NPRM published in 

the Federal Register on February 22, 

2012 (77 FR 10403). That NPRM 

proposed to continue to require revising 

the Airworthiness Limitations Section 

of the MPD document. That NPRM also 

proposed to require revising the 

maintenance program to incorporate an 

additional limitation, which terminates 

the existing requirements; and adding 

airplanes to 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 10403, 

February 22, 2012) and the FAA’s 

response to each comment. 

Request To Reduce the Scope of the 

NPRM (77 FR 10403, February 22, 

2012) 

ABX Air requested that we reduce the 

scope of the NPRM (77 FR 10403, 

February 22, 2012). 

ABX Air stated that the ‘‘SUMMARY’’ 

and ‘‘Actions Since Existing AD was 

Issued’’ sections of the NPRM imply 

that it is a result of an unsafe condition 

relating to certain cargo doors and flaps. 

ABX Air stated that the NPRM would 

require incorporation of the July 2011 

revision of Section 9 of the Boeing 767 

MPD Document into the operator’s 

maintenance program. ABX Air stated 

that requiring the complete revision is 

overreaching the AD’s scope. 

We disagree with reducing the scope 

of this final rule. The NPRM (77 FR 

10403, February 22, 2012) stated that reevaluation of certain doors and flaps 

prompted the new rulemaking. 

However, the re-evaluation was not 

limited to certain doors and flaps, but 

rather a complete review of the entire 

July 2011 revision of Subsection B, 

Airworthiness Limitations—Structural 

Limitations, of Section 9 of the Boeing 

767 MPD Document. The AD is 

intended to detect and correct fatigue 

cracking of the principal structural 

elements (PSEs) listed in the July 2011 

revision of Subsection B, Airworthiness 

Limitations—Structural Limitations, of 

Section 9 of the Boeing 767 MPD 


emcdonald on DSK67QTVN1PROD with RULES