65616 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 

(i) Related Information 

For more information about this AD, 

contact Katheryn Malatek, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7747; fax: 781–238– 

7199; email: katheryn.malatek@faa.gov. 

(j) Material Incorporated by Reference 

None. 

Issued in Burlington, Massachusetts, on 

October 21, 2015. 

Colleen M. D’Alessandro, 

Directorate Manager, Engine & Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–27184 Filed 10–26–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0498; Directorate 

Identifier 2014–NM–152–AD; Amendment 

39–18305; AD 2015–22–01] 

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) 2007–16– 

08, which applied to all The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–300, 747–400, 747–400D, and 

747SR series airplanes. AD 2007–16–08 

required repetitive inspections for 

cracking of the station 800 frame 

assembly, and repair if necessary. This 

new AD continues to require repetitive 

inspections for cracking of the station 

800 frame assembly, and repair if 

necessary, and expands the inspection 

area. This AD was prompted by reports 

of cracks found at the forward and aft 

inner chord strap and angles on the 

station 800 frame on the left-side and 

right-side main entry doors. We are 

issuing this AD to detect and correct 

fatigue cracks that could extend and 

fully sever the frame, which could result 

in development of skin cracks that 

could lead to rapid depressurization of 

the airplane. 

DATES: This AD is effective December 1, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 1, 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.govby searching for 

and locating Docket No. FAA–2015– 

0498. 

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– 

0498; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: Bill 

Ashforth, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6432; fax: 425– 

917–6590; email: bill.ashforth@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2007–16–08, 

Amendment 39–15147 (72 FR 44728, 

August 9, 2007). AD 2007–16–08 

applied to all The Boeing Company 

Model 747–100, 747–100B, 747–100B 

SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, and 747SR series 

airplanes. The NPRM published in the 

Federal Register on March 30, 2015 (80 

FR 16606). The NPRM was prompted by 

reports of cracks found at the forward 

and aft inner chord strap and angles on 

the station 800 frame on the left-side 

and right-side main entry doors. The 

NPRM proposed to continue to require 

repetitive inspections for cracking of the 

station 800 frame assembly, and repair 

if necessary, and expand the inspection 

area. We are issuing this AD to detect 

and correct fatigue cracks that could 

extend and fully sever the frame, which 

could result in development of skin 

cracks that could lead to rapid 

depressurization 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 (80 FR 16606, 

March 30, 2015) and the FAA’s response 

to each comment. 

Support for the NPRM (80 FR 16606, 

March 30, 2015) 

Boeing stated that it concurred with 

the contents of the NPRM (80 FR 16606, 

March 30, 2015). 

Statement Regarding the NPRM (80 FR 

16606, March 30, 2015) 

United Airlines stated that it has 

reviewed the NPRM (80 FR 16606, 

March 30, 2015), and has no comment 

to submit. 

Request To Clarify Inspection 

Requirements 

UPS requested that we add an 

additional statement to paragraph (i) of 

the proposed AD (‘‘Exception to the 

Service Information,’’) to clarify that the 

removal of fasteners is not required for 

performing the surface high-frequency 

eddy current (HFEC) inspections 

specified by paragraph (g) of the 

proposed AD (80 FR 16606, March 30, 

2015). UPS stated that by adding the 

clarification that the removal of 

fasteners is not required, significant 

time and materials would be saved by 

operators when accomplishing this 

inspection and prevent unnecessary 

alternative method of compliance 

(AMOC) requests. UPS explained that 

Boeing agreed in a response to a service 

request that fastener removal is not 

required for performing surface HFEC 

inspections. 

We agree because the clarification 

will reduce costs while ensuring the 

same level of safety. We have added the 

following sentence to paragraph (g) of 

this AD: ‘‘It is not necessary to remove 

fasteners while performing the surface 

HFEC inspections.’’ 

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 change described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (80 FR 


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Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 65617 

16606, March 30, 2015) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (80 FR 16606, 

March 30, 2015). 

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 Alert Service 

Bulletin 747–53A2451, Revision 2, 

dated June 13, 2014. The service 

information describes procedures for 

accomplishing repetitive inspections for 

cracking of the station 800 frame 

assembly, and repair. 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 124 

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 

Repetitive inspections Up to 53 work-hours × $85 per hour = $4,505 per inspection cycle.$0 Up to $4,505 per inspection cycle.Up to $558,620 per 

inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

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) 

2007–16–08, Amendment 39–15147 (72 

FR 44728, August 9, 2007), and adding 

the following new AD: 

2015–22–01 The Boeing Company: 

Amendment 39–18305; Docket No. 

FAA–2015–0498; Directorate Identifier 

2014–NM–152–AD. 

(a) Effective Date 

This AD is effective December 1, 2015. 

(b) Affected ADs 

This AD replaces AD 2007–16–08, 

Amendment 39–15147 (72 FR 44728, August 

9, 2007). 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 747–100, 747–100B, 747– 

100B SUD, 747–200B, 747–200C, 747–300, 

747–400, 747–400D, and 747SR series 

airplanes, certificated in any category. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of cracks 

found on the station 800 frame on the leftside and right-side main entry doors (MED), 

at the forward and aft inner chord strap and 

angles, which are outside the inspection area 

of AD 2007–16–08, Amendment 39–15147 

(72 FR 44728, August 9, 2007). We are 

issuing this AD to detect and correct fatigue 

cracks that could extend and fully sever the 

frame, which could result in development of 

skin cracks that could lead to rapid 

depressurization of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections of Station 800 Frame 

Assembly Between Stringer 14 and Stringer 

30 

Except as required by paragraph (i) of this 

AD, at the applicable time specified in 

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

Alert Service Bulletin 747–53A2451, 

Revision 2, dated June 13, 2014: Do a 

detailed inspection for cracking in the inner 

chord strap, angles, and exposed web 

adjacent to the inner chords, and do surface 

and open hole high-frequency eddy current 

(HFEC) inspections for cracking in the inner 

chord strap and angles of the station 800 

frame assembly between stringer 14 and 

stringer 30, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2451, Revision 2, 

dated June 13, 2014. It is not necessary to 

remove fasteners while performing the 

surface HFEC inspections. Repeat the 

inspections at the applicable times specified 

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

Alert Service Bulletin 747–53A2451, 

Revision 2, dated June 13, 2014. 

(h) Repair of Cracking 

If any cracking is found during any 

inspection required by paragraph (g) of this 

AD, before further flight, repair the cracking 

using a method approved in accordance with 


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65618 Federal Register / Vol. 80, No. 207 / Tuesday, October 27, 2015 / Rules and Regulations 

the procedures specified in paragraph (k) of 

this AD. 

(i) Exception to the Service Information 

(1) Where Boeing Alert Service Bulletin 

747–53A2451, Revision 2, dated June 13, 

2014, specifies a compliance time ‘‘after the 

Revision 2 date of this service bulletin,’’ this 

AD requires compliance within the specified 

time after the effective date of this AD. 

(2) The Condition column of paragraph 

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

Service Bulletin 747–53A2451, Revision 2, 

dated June 13, 2014, refers to total flight 

cycles ‘‘as of the Revision 2 date of this 

service bulletin.’’ This AD, however applies 

to airplanes with the specified total flight 

cycles or total flight hours as of the effective 

date of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for the 

inspections and repairs of the inner chord 

strap and angles of the station 800 frame 

assembly between stringer 14 and stringer 18 

required by paragraphs (g) and (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–53A2451, Revision 1, 

dated November 10, 2005, which was 

incorporated by reference in AD 2006–12–12, 

Amendment 39–14638 (71 FR 33595, June 

12, 2006). 

(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 for AD 2007–16–08, 

Amendment 39–15147 (72 FR 44728, August 

9, 2007), are approved as AMOCs for the 

corresponding provisions of this AD. 

(l) Related Information 

(1) For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@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 Alert Service Bulletin 747– 

53A2451, Revision 2, dated June 13, 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 October 

19, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–26979 Filed 10–26–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–4345; Directorate 

Identifier 2015–SW–049–AD; Amendment 

39–18306; AD 2015–22–02] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

emergency airworthiness directive (AD) 

No. 2015–16–51 (Emergency AD 2015– 

16–51) for Bell Helicopter Textron 

Canada Limited (Bell) Model 429 

helicopters. Emergency AD 2015–16–51 

required inspections of each inboard 

and outboard tail rotor pitch link 

assembly for axial or radial bearing play, 

and if there was axial or radial bearing 

play, removing the tail rotor pitch link 

and inspecting for wear. Emergency AD 

2015–16–51 was prompted by several 

reports of worn tail rotor pitch link 

spherical bearings. We are issuing this 

supersedure to retain the inspection 

requirements in Emergency AD 2015– 

16–51 while revising the applicability 

and compliance time to clarify that all 

Bell Model 429 helicopters require 

recurring inspections regardless of 

hours time-in-service (TIS) accumulated 

on the helicopter. These actions are 

intended to prevent pitch link failure 

and subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective 

November 12, 2015. 

We must receive comments on this 

AD by December 28, 2015. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address 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– 

4345; 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 Transport Canada 

Emergency AD, the economic 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations Office (telephone 

800–647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. For 

service information identified in this 

AD, contact Bell Helicopter Textron 

Canada Limited, 12,800 Rue de l’Avenir, 

Mirabel, Quebec J7J1R4; telephone (450) 

437–2862 or (800) 363–8023; fax (450) 

433–0272; or at http://

www.bellcustomer.com/files/. You may 

review the referenced service 

information at the FAA, Office of the 


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