8138 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1138; fax 425–227–1149. 

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

AMOC-REQUESTS@faa.gov. 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, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(q) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0274, dated 

November 15, 2013, 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–2016–0467. 

(r) 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 February 2, 2016 (80 FR 

81174, December 29, 2015). 

(i) Airbus Service Bulletin A330–29–3122, 

dated October 25, 2012. 

(ii) Airbus Service Bulletin A330–29–3126, 

dated June 12, 2014. 

(iii) Airbus Service Bulletin A340–29– 

4093, dated October 25, 2012. 

(iv) Airbus Service Bulletin A340–29– 

4097, dated June 12, 2014. 

(v) Airbus Service Bulletin A340–29–5021, 

dated October 2, 2012. 

(vi) Airbus Service Bulletin A340–29– 

5025, dated June 16, 2014. 

(vii) Hamilton Sundstrand Service Bulletin 

ERPS06M–29–19, dated August 6, 2012. 

(4) For Airbus service information 

identified in this AD, contact Airbus SAS, 

Airworthiness Office—EAL, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

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

5 61 93 45 80; email airworthiness.A330- 

A340@airbus.com; Internet http://

www.airbus.com. 

(5) For Hamilton Sundstrand service 

information identified in this AD, contact 

Hamilton Sundstrand, Technical 

Publications, Mail Stop 302–9, 4747 Harrison 

Avenue, P.O. Box 7002, Rockford, IL 61125– 

7002; telephone 860–654–3575; fax 860–998– 

4564; email tech.solutions@hs.utc.com; 

Internet http://

www.hamiltonsundstrand.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 February 

8, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03215 Filed 2–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3630; Directorate 

Identifier 2014–NM–253–AD; Amendment 

39–18397; AD 2016–04–03] 

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 all The 

Boeing Company Model 747–400F 

series airplanes. This AD was prompted 

by an analysis of the production 

methods used to increase fatigue 

resistance of the upper closure fittings at 

the nose cargo door portal’s C–3 frame, 

which showed that cracking could start 

too early to be caught in a timely 

manner by the inspection or 

maintenance program. This AD requires 

inspections of the upper closure fitting 

and connected strap and doubler at the 

nose cargo door portal for cracking, and 

related investigative and corrective 

actions if necessary. We are issuing this 

AD to detect and correct such cracking, 

which could result in sudden 

decompression and loss of the airplane’s 

structural integrity. 

DATES: This AD is effective March 24, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 24, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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–2015– 

3630. 

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– 

3630; 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: 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 by adding an AD that would 

apply to all The Boeing Company Model 

747–400F series airplanes. The NPRM 

published in the Federal Register on 

September 15, 2015 (80 FR 55273) (‘‘the 

NPRM’’). The NPRM was prompted by 

a report indicating that an analysis of 

the production methods used to 

increase fatigue resistance of the upper 

closure fittings at the nose cargo door 

portal’s C–3 frame showed that cracking 

could start too early to be caught in a 

timely manner by the inspection or 

maintenance program. The upper 

closure fittings used in the nose cargo 

door portal C–3 frame were shot peened 

to increase fatigue resistance. However, 

an analysis showed that the increase in 


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Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 8139 

fatigue resistance was still not enough to 

ensure that cracking would be caught by 

the inspection program specified in the 

Boeing 747–400 maintenance planning 

data (MPD) document. The NPRM 

proposed to require inspections of the 

upper closure fitting and connected 

strap and doubler at the nose cargo door 

portal for cracking, and related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

detect and correct such cracking, which 

could result in sudden decompression 

and loss of the airplane’s structural 

integrity. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comment received. 

Boeing supported the NPRM. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, 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 for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2880, dated December 

3, 2014. This service information 

describes procedures for a detailed 

inspection of the upper closure fitting 

and connected strap and doubler, a 

surface high frequency eddy current 

(HFEC) inspection of the upper closure 

fitting for cracking, 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. 

Costs of Compliance 

We estimate that this AD affects 38 

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 

Inspections ...................... 9 work-hours × $85 per hour = $765 per inspection 

cycle.

$0 $765 per inspection cycle $29,070 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs or replacements 

that would be required based on the 

results of the inspection. Parts costs 

could be up to $42,930 per airplane. We 

have no way of determining the number 

of work hours (because the type of 

repair will vary depending on findings) 

or the number of aircraft that might 

need the repairs or replacements. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

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): 

2016–04–03 The Boeing Company: 

Amendment 39–18397; Docket No. 

FAA–2015–3630; Directorate Identifier 

2014–NM–253–AD. 

(a) Effective Date 

This AD is effective March 24, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 747–400F series airplanes, 

certificated in any category, as identified in 

paragraph 1.A., ‘‘Effectivity,’’ of Boeing Alert 

Service Bulletin 747–53A2880, dated 

December 3, 2014. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by a report that an 

analysis of the production methods used to 

increase fatigue resistance of the upper 

closure fittings at the nose cargo door portal’s 

C–3 frame showed that cracking could still 

start too early to be caught in a timely 


wgreen on DSK2VPTVN1PROD with RULES
8140 Federal Register / Vol. 81, No. 32 / Thursday, February 18, 2016 / Rules and Regulations 

manner by the inspection or maintenance 

program. We are issuing this AD to detect 

and correct such cracking, which could result 

in sudden decompression and loss of the 

airplane’s structural integrity. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions 

Except as required by paragraph (h) of this 

AD: At the applicable time specified in 

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

Alert Service Bulletin 747–53A2880, dated 

December 3, 2014, do a detailed inspection 

of the upper closure fitting, strap, and 

doubler and a surface high frequency eddy 

current (HFEC) inspection of the upper 

closure fitting at the nose cargo door portal 

for cracking, and do all applicable related 

investigative and corrective actions, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2880, dated December 3, 2014. 

Repeat the inspections at the time specified 

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

Alert Service Bulletin 747–53A2880, dated 

December 3, 2014. Do the applicable related 

investigative and corrective actions at the 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–53A2880, dated December 3, 

2014. 

(h) Exceptions to the Service Information 

(1) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 747–53A2880, 

dated December 3, 2014, refers to a 

compliance time ‘‘after the original issue date 

of this service bulletin,’’ this AD requires 

compliance within the specific compliance 

time after the effective date of this AD. 

(2) If any crack is found during any 

inspection required by this AD, and Boeing 

Alert Service Bulletin 747–53A2880, dated 

December 3, 2014, specifies to contact Boeing 

for appropriate action: Before further flight, 

repair the cracking using a method approved 

in accordance with the procedures specified 

in paragraph (i) of this AD. 

(i) 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 (j)(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, 

modification, or alteration 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 method, 

modification deviation, or alteration 

deviation must meet the certification basis of 

the airplane, and the approval must 

specifically refer to this AD. 

(4) Except as required by paragraph (h)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (i)(4)(i) and (i)(4)(ii) of this AD 

apply. 

(i) The steps labeled as RC, including 

substeps under an RC step and any figures 

identified in an RC step, must be done to 

comply with the AD. An AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures. 

(ii) Steps not labeled as RC may be 

deviated from using accepted methods in 

accordance with the operator’s maintenance 

or inspection program without obtaining 

approval of an AMOC, provided the RC steps, 

including substeps and identified figures, can 

still be done as specified, and the airplane 

can be put back in an airworthy condition. 

(j) Related Information 

For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6432; fax: 425– 

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

(k) 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– 

53A2880, dated December 3, 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 

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 February 

8, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–03217 Filed 2–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2460; Directorate 

Identifier 2014–NM–163–AD; Amendment 

39–18396; AD 2016–04–02] 

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) 2010–26– 

10, which applied to certain The Boeing 

Company Model 747–200C, –200F, 

–400, –400D, and –400F series 

airplanes. AD 2010–26–10 required 

repetitive inspections for cracking of the 

lap joints, modification of certain lap 

joints, and certain post-repair 

inspections of the lap joints. This new 

AD adds new repetitive postmodification inspections for cracking in 

the lap joints, and repair if necessary. 

This AD was prompted by an evaluation 

by the design approval holder (DAH) 

which indicated that certain lap joints 

are subject to widespread fatigue 

damage (WFD). We are issuing this AD 

to detect and correct fatigue cracking in 

certain lap joints, which could result in 

rapid depressurization and consequent 

reduced structural integrity of the 

airplane. 

DATES: This AD is effective March 24, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 24, 2016. 

ADDRESSES: For service information 

identified in this final rule, 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 


wgreen on DSK2VPTVN1PROD with RULES