Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 14707 

1.A., ‘‘Effectivity,’’ of GE GEnx–1B Service 

Bulletin 72–0309 R00, dated March 11, 2016, 

unless at least one engine has been reworked 

in accordance with paragraph 3.A.(1)(b), 3.B., 

or 3.C. of the Accomplishment Instructions of 

GE GEnx–1B Service Bulletin 72–0309 R00, 

dated March 11, 2016. 

(k) Reporting Provisions 

Although GE GEnx Service Bulletin GEnx– 

1B 72–0309 R00, dated March 11, 2016, 

specifies reporting certain tip clearance 

measurements to GE, this AD does not 

require any report. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m) 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. 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. 

(m) Related Information 

For more information about this AD, 

contact Sue Lucier, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6438; fax: 425– 

917–6590; email: Suzanne.Lucier@faa.gov. 

(n) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) GE GEnx–1B Service Bulletin 72–0309 

R00, dated March 11, 2016. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact General Electric Company, 

GE Aviation, Room 285, 1 Neumann Way, 

Cincinnati, OH 45215; phone: 513–552–3272; 

email: geae.aoc@ge.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 March 

14, 2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–06117 Filed 3–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0774; Directorate 

Identifier 2013–NM–154–AD; Amendment 

39–18438; AD 2016–06–07] 

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) 2006–22– 

15 for all 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. AD 

2006–22–15 required repetitive 

inspections for cracking of certain panel 

webs and stiffeners of the nose wheel 

well (NWW), and corrective actions if 

necessary; and replacement of certain 

panels with new panels, which 

terminates the repetitive inspections. 

This new AD reduces a compliance time 

and adds certain inspections and an 

applicable repair. This AD was 

prompted by multiple reports of fatigue 

cracking in the NWW top panel and side 

panel webs and stiffeners. We are 

issuing this AD to prevent fatigue 

cracking of the NWW side and top 

panels, which could result in a NWW 

depressurization event severe enough to 

reduce the structural integrity of the 

fuselage. 

DATES: This AD is effective April 22, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 22, 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–2014– 

0774. 

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– 

0774; 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 supplemental notice of 

proposed rulemaking (SNPRM) to 

amend 14 CFR part 39 to supersede AD 

2006–22–15, Amendment 39–14812 (71 

FR 64884, November 6, 2006) (‘‘AD 

2006–22–15’’). AD 2006–22–15 applied 

to all 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. The SNPRM 

published in the Federal Register on 

September 18, 2015 (80 FR 56407) (‘‘the 

SNPRM’’). We preceded the SNPRM 

with a notice of proposed rulemaking 

(NPRM) that published in the Federal 

Register on November 17, 2014 (79 FR 

68388) (‘‘the NPRM’’). The NPRM 

proposed to continue to require 

repetitive inspections for cracking of 


asabaliauskas on DSK3SPTVN1PROD with RULES
14708 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 

certain panel webs and stiffeners of the 

NWW, and corrective actions if 

necessary; and replacement of certain 

panels with new panels, which 

terminates the repetitive inspections. 

The NPRM proposed to reduce a 

compliance time and add certain 

inspections and repair if necessary. The 

NPRM was prompted by reports of 

fatigue cracking in the panel webs and 

stiffeners of the NWW found prior to the 

inspection threshold of AD 2006–22–15. 

The SNPRM revised the NPRM by 

specifying a repetitive inspection 

interval for a certain NWW area 

inspection. We are issuing this AD to 

prevent fatigue cracking of the NWW 

side and top panels, which could result 

in a NWW depressurization event severe 

enough to reduce the structural integrity 

of the fuselage. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the SNPRM and the FAA’s 

response to each comment. 

Support for the SNPRM 

Two commenters supported the 

SNPRM. One commenter stated that the 

FAA should continue to execute its 

administrative power to ensure traveler 

safety and industry compliance, adding 

that while the original rule was good, 

ensuring that specifics are covered and 

timetables are available is an important 

improvement. 

Request for Credit for Compliance 

Times in Previously Approved 

Alternative Methods of Compliance 

(AMOCs) 

Boeing requested that we allow credit 

for the compliance times in previously 

approved AMOCs, if the compliance 

times are acceptable according to the 

SNPRM. 

We agree with the commenter’s 

request. We have revised paragraph 

(p)(4) of this AD to state that: AMOC 

actions approved previously for AD 

2006–22–15 are approved as AMOCs for 

the corresponding actions of this AD. In 

addition, paragraph (p)(4) of this AD 

states that the compliance times in 

AMOCs approved previously for AD 

2006–22–15 are not approved for the 

corresponding actions and compliance 

times in this AD, if this AD specifies an 

earlier compliance time than that 

specified in AD 2006–22–15; and that 

compliance times in AMOCs approved 

previously for AD 2006–22–15 that meet 

the requirements of this AD are 

acceptable. 

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 SNPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the SNPRM. 

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 the following Boeing 

service bulletins. 

• Boeing Alert Service Bulletin 747– 

53A2808, dated November 30, 2012. 

This service information describes 

procedures for replacement of the side 

and top panel webs, support beams, and 

stiffeners of the NWW; an inspection for 

cracking of the attaching structural 

elements that are common to the 

removed top and side panels of the 

NWW; repetitive post-modification 

inspections for cracks in the top and 

side panel webs and stiffeners; and 

repairs. 

• Boeing Service Bulletin 747– 

53A2465, Revision 5, dated July 11, 

2013. This service information describes 

procedures for doing inspections for 

cracking of the NWW side panel and top 

panel webs and longitudinal stiffeners 

for cracks, and related investigative and 

corrective actions. 

• Boeing Service Bulletin 747– 

53A2562, Revision 3, dated July 11, 

2013. This service information describes 

procedures for replacement of the side 

and top panel webs and certain 

stiffeners of the NWW; an inspection for 

cracks in attaching structural elements 

that are common to the removed top 

panel and side panels; repetitive postmodification inspections for cracks in 

the top and side panel webs and 

stiffeners; and repairs. 

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 will affect 

255 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 [actions retained from AD 2006– 

22–15].

119 work-hours × $85 per 

hour = $10,115 per inspection cycle.

$0 ...................................... $10,115 per inspection 

cycle.

$2,579,325 per inspection 

cycle. 

Modification [actions retained from AD 2006– 

22–15].

Up to 1,346 work-hours × 

$85 per hour = 

$114,410.

Up to $144,248 ................. Up to $258,658 ................. Up to $65,957,790. 

Post-modification Inspections [new action].119 work-hours × $85 per 

hour = $10,115 per inspection cycle.

$0 ...................................... $10,115 per inspection 

cycle.

$2,579,325 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 


asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 14709 

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) 

2006–22–15, Amendment 39–14812 (71 

FR 64884, November 6, 2006) (‘‘AD 

2006–22–15’’), and adding the following 

new AD: 

2016–06–07 The Boeing Company: 

Amendment 39–18438; Docket No. 

FAA–2014–0774; Directorate Identifier 

2013–NM–154–AD. 

(a) Effective Date 

This AD is effective April 22, 2016. 

(b) Affected ADs 

This AD replaces AD 2006–22–15, 

Amendment 39–14812 (71 FR 64884, 

November 6, 2006) (‘‘AD 2006–22–15’’). 

(c) Applicability 

This AD applies to all 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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by multiple reports 

of cracking in the nose wheel well (NWW) 

top panel and side panel webs and stiffeners. 

We are issuing this AD to prevent fatigue 

cracking of the NWW side and top panels, 

which could result in a NWW 

depressurization event severe enough to 

reduce the structural integrity of the fuselage. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Corrective 

Actions With New Compliance Times 

Except as specified in paragraphs (h)(1) 

and (h)(2) of this AD, at the applicable time 

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

Boeing Service Bulletin 747–53A2465, 

Revision 5, dated July 11, 2013: Do the 

actions specified in paragraphs (g)(1), (g)(2), 

and (g)(3) of this AD, and do all applicable 

related investigative and corrective actions; 

in accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 747– 

53A2465, Revision 5, dated July 11, 2013, 

except as specified in paragraph (h)(3) of this 

AD. Do all applicable related investigative 

and corrective actions before further flight. 

Repeat the inspections specified in 

paragraphs (g)(1), (g)(2), and (g)(3) of this AD 

thereafter at the applicable intervals specified 

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

Service Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013. The repetitive interval 

for the inspection of Area 2 specified in table 

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

Service Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013, is 1,000 flight cycles. In 

table 2 and table 3 in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013, the date ‘‘January 27, 2005,’’ is the 

effective date of AD 2004–25–23, 

Amendment 39–13911 (69 FR 76839, 

December 23, 2004); and the date ‘‘May 10, 

2005,’’ is the effective date of AD 2005–09– 

02, Amendment 39–14070 (70 FR 21141, 

April 25, 2005; corrected May 25, 2005 (70 

FR 29940)). 

(1) Do an external detailed inspection for 

cracks of the top and sidewall panel webs of 

the NWW (specified as Area 1 and Area 2 in 

Boeing Service Bulletin 747–53A2465, 

Revision 5, dated July 11, 2013). 

(2) Do internal detailed and surface high 

frequency eddy current (HFEC) inspections 

for cracks of the sidewall panel and top panel 

stiffeners of the NWW (specified as Area 3 in 

Boeing Service Bulletin 747–53A2465, 

Revision 5, dated July 11, 2013). 

(3) Do an external detailed and ultrasonic 

testing (UT) inspection for cracks of the top 

and sidewall panel webs of the NWW 

(specified as Area 1 and Area 2 in Boeing 

Service Bulletin 747–53A2465, Revision 5, 

dated July 11, 2013). 

(h) Exceptions to Boeing Service Bulletin 

747–53A2465, Revision 5, Dated July 11, 

2013 

(1) Table 1 in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013, applies to airplanes with less than 

15,000 total flight cycles ‘‘as of the Revision 

5 date of this service bulletin.’’ For this AD, 

however, table 1 applies to airplanes with the 

specified total flight cycles as of the effective 

date of this AD. 

(2) Table 1 in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013, specifies a compliance time of ‘‘13,000 

total flight-cycles,’’ or ‘‘within 1,000 flight 

cycles after the Revision 5 date of this service 

bulletin,’’ whichever occurs later. This AD 

requires compliance before the accumulation 

of 10,000 total flight cycles or within 1,000 

flight cycles after the effective date of this 

AD, whichever occurs later. 

(3) If any cracking or damage is found 

during any inspection required by paragraph 

(g) of this AD, and Boeing Service Bulletin 

747–53A2465, Revision 5, dated July 11, 

2013, specifies to contact Boeing for 

appropriate action: Before further flight, 

repair the cracking or damage using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. 

(i) NWW Modification 

For airplanes identified in Boeing Service 

Bulletin 747–53A2562, Revision 3, dated July 

11, 2013: At the applicable time specified in 

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

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013, replace the left-side, 

right-side, and top panels of the NWW, as 

applicable, with new panels, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013. As of the 

effective date of this AD, concurrently with 

doing the replacement specified in Boeing 

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013, do a detailed inspection 

for any cracks or damage (including, but not 

limited to, dents and corrosion) in all 

attaching structural elements that are 

common to the removed top panel and side 

panels, as applicable, and do all applicable 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013. If any crack or damage 

is found, before further flight, repair the 

cracking or damage using a method approved 

in accordance with the procedures specified 

in paragraph (p) of this AD. In paragraph 1.E., 

‘‘Compliance,’’ of Boeing Service Bulletin 

747–53A2562, Revision 3, dated July 11, 

2013, the date ‘‘December 11, 2006,’’ is the 

effective date of AD 2006–22–15. 


asabaliauskas on DSK3SPTVN1PROD with RULES
14710 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 

(j) Repetitive Post-Modification Inspections 

For airplanes on which the replacement 

specified in paragraph (i) of this AD has been 

done: Except as required by paragraph (k) of 

this AD, at the applicable time specified in 

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

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013, do the actions specified 

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

AD. If any crack is found: Before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. Repeat 

the inspections specified in paragraphs (j)(1), 

(j)(2), and (j)(3) of this AD thereafter at the 

applicable intervals specified in paragraph 

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

Bulletin 747–53A2562, Revision 3, dated July 

11, 2013. 

(1) Do an external detailed inspection for 

cracks in the side panel webs, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013. 

(2) Do an internal detailed inspection and 

high frequency eddy current (HFEC) 

inspection for cracks in the top and side 

panel stiffeners, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 747–53A2562, Revision 3, 

dated July 11, 2013. 

(3) Do an external detailed inspection for 

cracks in the top panel web, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013. 

(k) Exception to Boeing Service Bulletin 747– 

53A2562, Revision 3, Dated July 11, 2013 

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

Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013, specifies a 

compliance time relative to the ‘‘Revision 3 

date of this service bulletin,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(l) NWW Modification for Certain Airplanes 

For airplanes identified in Boeing Alert 

Service Bulletin 747–53A2808, dated 

November 30, 2012: At the applicable time 

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

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012, replace the left 

side, right side, and top panels of the NWW, 

as applicable, with new panels, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–53A2808, dated November 30, 2012. 

Concurrently with doing the replacement 

specified in this paragraph, do a detailed 

inspection for cracks of the attaching 

structural elements that are common to the 

removed top, left side, and right side panels 

of the NWW, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2808, dated 

November 30, 2012. If any crack is found, 

before further flight, repair the cracking using 

a method approved in accordance with the 

procedures specified in paragraph (p) of this 

AD. 

(m) Repetitive Post-Modification Inspections 

for Certain Airplanes 

For airplanes on which the replacement 

specified in paragraph (l) of this AD has been 

done: At the applicable time specified in 

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

Alert Service Bulletin 747–53A2808, dated 

November 30, 2012, do the actions specified 

in paragraphs (m)(1), (m)(2), and (m)(3) of 

this AD. If any crack is found: Before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. Repeat 

the inspections specified in paragraphs 

(m)(1), (m)(2), and (m)(3) of this AD 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 747–53A2808, dated 

November 30, 2012. 

(1) Do an external detailed inspection for 

cracks in the side panel webs, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012. 

(2) Do an internal detailed inspection and 

HFEC inspection for cracks in the top and 

side panel stiffeners, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–53A2808, dated 

November 30, 2012. 

(3) Do an external detailed inspection for 

cracks in the top panel web, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 747–53A2808, 

dated November 30, 2012. 

(n) Terminating Action for Certain 

Repetitive Inspections 

Replacing the left side, right side, and top 

panels of the NWW with new panels as 

specified in paragraph (i) or (l) of this AD 

terminates the repetitive inspections required 

by paragraph (g) of this AD. 

(o) Credit for Previous Actions 

(1) This paragraph restates the credit given 

in paragraph (k) of AD 2006–22–15. 

(i) This paragraph provides credit for the 

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

AD, if those actions were performed before 

January 27, 2005 (the effective date of AD 

2004–25–23, Amendment 39–13911 (69 FR 

76839, December 23, 2004)), using Boeing 

Alert Service Bulletin 747–53A2465, dated 

April 5, 2001, which is not incorporated by 

reference in this AD. 

(ii) This paragraph provides credit for 

actions required by paragraphs (g)(1) and 

(g)(2) of this AD, if those actions were 

performed before December 11, 2006 (the 

effective date of AD 2006–22–15), using a 

service bulletin identified in paragraph 

(o)(1)(ii)(A), (o)(1)(ii)(B), or (o)(1)(ii)(C) of this 

AD, which are not incorporated by reference 

in this AD. 

(A) Boeing Alert Service Bulletin 747– 

53A2465, Revision 1, dated October 16, 2003. 

(B) Boeing Alert Service Bulletin 747– 

53A2465, Revision 2, dated November 11, 

2004. 

(C) Boeing Alert Service Bulletin 747– 

53A2465, Revision 3, dated December 23, 

2004. 

(2) This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–53A2465, Revision 4, 

dated February 24, 2005, which is not 

incorporated by reference in this AD. 

(3) This paragraph provides credit for the 

actions required by paragraphs (i) and (j) of 

this AD, if those actions were performed 

before the effective date of this AD using the 

service information identified in paragraph 

(o)(3)(i) or (o)(3)(ii) of this AD. 

(i) Boeing Service Bulletin 747–53A2562, 

Revision 1, dated July 28, 2005, which was 

incorporated by reference in AD 2006–22–15. 

(ii) Boeing Service Bulletin 747–53A2562, 

Revision 2, dated May 31, 2007, which is not 

incorporated by reference in this AD. 

(p) 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 (q)(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. 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) AMOC actions approved previously for 

AD 2006–22–15 are approved as AMOCs for 

the corresponding actions of this AD. The 

compliance times in AMOCs approved 

previously for AD 2006–22–15 are not 

approved for the corresponding actions and 

compliance times in this AD, if this AD 

specifies an earlier compliance time than that 

specified in AD 2006–22–15. Compliance 

times in AMOCs approved previously for AD 

2006–22–15 that meet the requirements of 

this AD are acceptable. 

(q) Related Information 

(1) 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. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(r) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 


asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 14711 

(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– 

53A2808, dated November 30, 2012. 

(ii) Boeing Service Bulletin 747–53A2465, 

Revision 5, dated July 11, 2013. 

(iii) Boeing Service Bulletin 747–53A2562, 

Revision 3, dated July 11, 2013. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at 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 March 9, 

2016. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–06001 Filed 3–17–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–0495; Directorate 

Identifier 2014–NM–172–AD; Amendment 

39–18435; AD 2016–06–04] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–300, 

–400, and –500 series airplanes. This 

AD was prompted by reports of cracking 

at certain fastener locations in the 

window corners of the window belt 

area. This AD requires repetitive high 

frequency eddy current (HFEC) 

inspections for fatigue cracking in 

certain fastener locations in the window 

corners of the window belt area, and 

related investigative and corrective 

actions if necessary. This AD also 

provides an optional preventive 

modification that terminates the 

inspections at the modified location. We 

are issuing this AD to detect and correct 

fatigue cracking around fastener 

locations that could cause multiple 

window corner skin cracks, which 

could result in rapid decompression and 

loss of structural integrity of the 

airplane. 

DATES: This AD is effective April 22, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of April 22, 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– 

0495. 

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– 

0495; 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: 

Jennifer Tsakoumakis, Aerospace 

Engineer, Airframe Branch, ANM–120L, 

FAA, Los Angeles Aircraft Certification 

Office (ACO), 3960 Paramount 

Boulevard, Lakewood, CA 90712–4137; 

phone: 562–627–5264; fax: 562–627– 

5210; email: jennifer.tsakoumakis@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 737–300, –400, and –500 series 

airplanes. The NPRM published in the 

Federal Register on March 24, 2015 (80 

FR 15523) (‘‘the NPRM’’). The NPRM 

was prompted by reports of cracking at 

certain fastener locations in the window 

corners of the window belt area. The 

NPRM proposed to require repetitive 

HFEC inspections for fatigue cracking in 

certain fastener locations in the window 

corners of the window belt area, and 

related investigative and corrective 

actions if necessary. We are issuing this 

AD to detect and correct fatigue 

cracking around fastener locations that 

could cause multiple window corner 

skin cracks, which could result in rapid 

decompression and loss of structural 

integrity 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 and the FAA’s 

response to each comment. 

Request for Clarification of Location of 

the Twelve Fastener Inspections 

Southwest Airlines (SWA) requested 

that a correction be made to paragraph 

(g) of the proposed AD to clarify the 

areas for the inspection of the twelve 

fastener locations. SWA noted that 

paragraph (g) of the proposed AD stated 

to inspect locations ‘‘at the upper 

forward and lower aft corners of each 

window between station (STA) 360 and 

STA 540 and between STA 727 and 

STA 908.’’ SWA stated that between 

STA 727 and STA 908, Boeing Alert 

Service Bulletin 737–53A1328, dated 

July 22, 2014, specifies the location as 

the lower forward and upper aft corners. 

We agree with the commenter for the 

reason provided. We have revised 

paragraph (g) of this AD to require an 

inspection of the twelve fastener 

locations at the upper forward and 

lower aft corners of each window 

between STA 360 and STA 540 and at 

the upper aft and lower forward corners 

of each window between STA 727 and 

STA 908. 

Request for Clarification of the Intent of 

the Inspection Requirements in 

Paragraph (g) of the Proposed AD 

SWA requested that we clarify the 

intent of paragraph (g) of the proposed 

AD. SWA stated that paragraph (g) of 

the proposed AD states to accomplish 

the inspections at the times specified in 

tables 1 and 2 of paragraph 1.E., 


asabaliauskas on DSK3SPTVN1PROD with RULES