Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules 1577 

Issued in Renton, Washington, on 

December 23, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–33175 Filed 1–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8429; Directorate 

Identifier 2015–NM–122–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–100, 

747–100B, 747–100B SUD, 747–200B, 

747–200C, 747–200F, 747–300, 747– 

400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes. This proposed 

AD was prompted by reports of fatigue 

cracks in the station 320 crown frame 

and in window post number 3. This 

proposed AD would require repetitive 

inspections for cracks and missing 

fasteners of the station 320 crown frame, 

cracks in the web and flange surfaces of 

the forward segment of window post 

number 3, and missing fasteners and 

cracks of the window upper sill; postmodification inspections for cracks of 

the window upper sill; one-time 

fastener rework; and related 

investigative and corrective actions if 

necessary. We are proposing this AD to 

detect and correct fatigue cracking and 

missing fasteners of the station 320 

crown frame, cracking of the window 

post number 3, and cracking of the 

window upper sill, which could result 

in an in-flight decompression and a loss 

of structural integrity of the fuselage. 

DATES: We must receive comments on 

this proposed AD by February 29, 2016. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8429. 

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– 

8429; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–8429; Directorate Identifier 2015– 

NM–122–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received reports of fatigue 

cracks in the station 320 crown frame on 

Model 747–400 series airplanes. Other 

Model 747 airplanes, except Model 747– 

8F and 747–8 airplanes, are of a similar 

station 320 crown frame configuration. 

Inner chord cracks of 0.03- to 0.22-inch 

in length have been found on 15 

airplanes with total flight cycles ranging 

from 11,498 to 31,315. Also, a 1.8-inch 

crack was found in the outboard web of 

the frame on one airplane with 14,749 

total flight cycles. 

Cracks have also been found in 

window post number 3, which connects 

to the lower end of the inner chord of 

the station 320 crown frame. Cracks of 

0.03- to 0.11-inch in length have been 

found in window post number 3 on five 

airplanes with total flight cycles ranging 

from 12,329 to 15,772. 

Additionally, fatigue cracks that had 

extended to fully sever the inner chord 

and outboard web of the frame were 

found on the Model 747–400 fatigue test 

airplane at 38,333 total pressure cycles, 

and significant cracks were found in 

both the frame inner chord and 

outboard web at 30,500 total pressure 

cycles on the Model 747–100SR fatigue 

test airplane. 

Fatigue cracking and missing 

fasteners of the station 320 crown frame, 

cracking of the window post number 3, 

and cracking of the window upper sill 

could result in in-flight decompression 

and a loss of structural integrity of the 

fuselage. 

Related Service Information Under 

1 CFR Part 51 

We reviewed Boeing Alert Service 

Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015. The service 

information describes procedures for 

inspections and corrective actions for 

cracks and missing fasteners in the 

inner chord and outboard webs of the 

station 320 crown frame, in the left and 

right side window post number 3, and 

in the upper sill structure. 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 NPRM. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
1578 Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions identified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ For 

information on the procedures and 

compliance times, see this service 

information at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8429. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Differences Between This Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 747– 

53A2862, Revision 1, dated July 24, 

2015, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as 

Required for Compliance (RC) in any 

service information identified 

previously have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

For service information that contains 

steps that are labeled as RC, the 

following provisions apply: (1) 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, and an 

alternative method of compliance 

(AMOC) is required for any deviations 

to RC steps, including substeps and 

identified figures; and (2) 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. 

Costs of Compliance 

We estimate that this proposed AD 

affects 165 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

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

Inspections ........ Up to 193 work-hours × $85 per hour = $16,405 

per inspection cycle.

$0 Up to $16,405 per inspection cycle.Up to $2,706,825 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 proposed 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 determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

the 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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. 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 81, No. 8 / Wednesday, January 13, 2016 / Proposed Rules 1579 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

The Boeing Company: Docket No. FAA– 

2015–8429; Directorate Identifier 2015– 

NM–122–AD. 

(a) Comments Due Date 

We must receive comments by February 

29, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 747–100, 747–100B, 747–100B SUD, 

747–200B, 747–200C, 747–200F, 747–300, 

747–400, 747–400D, 747–400F, 747SR, and 

747SP series airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracks in the station 320 crown frame 

in window post number 3. We are issuing 

this AD to detect and correct fatigue cracking 

and missing fasteners of the station 320 

crown frame, cracking of the window post 

number 3, and cracking of the window upper 

sill, which could result in an in-flight 

decompression and a loss of structural 

integrity of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Initial Inspections, Related Investigative 

Actions, and Corrective Actions 

At the applicable time specified in 

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

Alert Service Bulletin 747–53A2862, 

Revision 1, dated July 24, 2015, except as 

provided by paragraphs (j)(1) and (j)(2) of this 

AD: Do the actions specified in paragraphs 

(g)(1) through (g)(5) of this AD; and do all 

applicable related investigative and 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015, except as required by 

paragraph (j)(3) of this AD. Do all applicable 

related investigative and corrective actions 

before further flight. 

(1) Do a detailed inspection for cracks and 

missing fasteners of the station 320 crown 

frame. 

(2) Do a surface high frequency eddy 

current (HFEC) inspection for cracks of the 

station 320 crown frame. 

(3) Do a surface HFEC inspection for cracks 

in the web and flange surfaces of the forward 

segment of window post number 3. 

(4) Do a detailed inspection for missing 

fasteners of the window upper sill. 

(5) Do a surface HFEC inspection for cracks 

of the window upper sill. 

(h) Repetitive Inspections and Post-Repair 

Inspections, Related Investigative Actions, 

and Corrective Actions 

Do applicable repetitive post-repair 

inspections and repeat the inspections 

specified in paragraphs (g)(1) through (g)(5) 

of this AD for cracking in the window upper 

sill thereafter at the applicable compliance 

time and intervals specified in paragraph 

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

Bulletin 747–53A2862, Revision 1, dated July 

24, 2015; and do all applicable related 

investigative and corrective actions; in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2862, Revision 1, dated July 24, 

2015, except as required by paragraph (j)(3) 

of this AD. Do all applicable related 

investigative and corrective actions before 

further flight. 

(i) Fastener Rework, Related Investigative 

Actions, and Corrective Actions 

At the applicable time specified in 

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

Alert Service Bulletin 747–53A2862, 

Revision 1, dated July 24, 2015: Do the 

applicable actions (including fastener rework 

and a detailed inspection of the condition of 

the fastener hole) specified in Part 11 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2862, Revision 1, 

dated July 24, 2015; and do all applicable 

related investigative and corrective actions; 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2862, Revision 1, dated July 24, 

2015. Do all applicable related investigative 

and corrective actions before further flight. 

(j) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

747–53A2862, Revision 1, dated July 24, 

2015, specifies a compliance time ‘‘after the 

original date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(2) Where Boeing Alert Service Bulletin 

747–53A2862, Revision 1, dated July 24, 

2015, specifies a compliance time ‘‘after the 

Revision 1 date of this service bulletin,’’ this 

AD requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(3) Where Boeing Alert Service Bulletin 

747–53A2862, Revision 1, dated July 24, 

2015, specifies to contact Boeing for repairs: 

Before further flight, repair, using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(k) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

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

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

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

modification, or alteration required by this 

AD if it is approved the Boeing Commercial 

Airplanes Organization Designation 

Authorization (ODA) that has been 

authorized by the Manager, Seattle ACO, to 

make those findings. 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 paragraphs (g), 

(h), and (j)(3) of this AD: For service 

information that contains steps that are 

labeled as Required for Compliance (RC), the 

provisions of paragraphs (k)(4)(i) and 

(k)(4)(ii) 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. 

(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) 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. 

Issued in Renton, Washington, on 

December 23, 2015. 

John P. Piccola, Jr., 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–33172 Filed 1–12–16; 8:45 am] 

BILLING CODE 4910–13–P 


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