14704 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 

(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): 

2016–06–06 Quest Aircraft Design, LLC: 

Amendment 39–18437; Docket No. 

FAA–2015–5318; Directorate Identifier 

2015–CE–035–AD. 

(a) Effective Date 

This AD is effective April 22, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Quest Aircraft Design, 

LLC Model KODIAK 100 airplanes, all serial 

numbers 100–0001 through 100–0149, that 

are certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 2730; Elevator Control System. 

(e) Unsafe Condition 

This AD was prompted by a report of 

limited control yoke movement due to 

cushion edging jammed in the elevator 

control anti-rotation guide slot. We are 

issuing this AD to prevent failure of the 

elevator control system, which could result 

in loss of control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspect Cushion Edging 

Before further flight April 22, 2016 (after 

the effective date of this AD) and repetitively 

thereafter at intervals not to exceed 50 hours 

time-in-service until the terminating action 

specified in paragraph (i) of this AD is done, 

inspect the cushion edging, part number (P/ 

N) M22529/2–3R–25, located on each side of 

the elevator control anti-rotation guide slot, 

P/N 100–619–0008, for the pilot and co-pilot 

control yoke assemblies, following section 

5.1 Cushion Edging Inspection of Quest 

Aircraft Company Field Service Instruction, 

Elevator Control System—Cushion Edging 

Inspection, Report No. FSI–105, Revision 00, 

not dated, as specified in Quest Aircraft 

KODIAK Mandatory Service Bulletin SB14– 

07, dated August 26, 2014; and Quest Aircraft 

Company KODIAK 100 Mandatory Service 

Bulletin SB14–07, Revision 01, dated 

November 23, 2015. 

(h) Replace Cushion Edging 

If damage or wear is found during any 

inspection required in paragraph (g) of this 

AD, before further flight, replace the cushion 

edging following section 5.3 of Quest Aircraft 

Company Field Service Instruction, Elevator 

Control System—Cushion Edging Inspection, 

Report No. FSI–105, Revision 00, not dated, 

as specified in Quest Aircraft KODIAK 

Mandatory Service Bulletin SB14–07, dated 

August 26, 2014; and Quest Aircraft 

Company KODIAK 100 Mandatory Service 

Bulletin SB14–07, Revision 01, dated 

November 23, 2015. 

(i) Install Wear Pads (Terminating Action for 

the Repetitive Inspections) 

Within 1 year after April 22, 2016 (the 

effective date of this AD), remove the cushion 

edging, P/N M22529/2–3R–25, installed on 

the elevator control anti-rotation guide, and 

install wear pads, P/N 100–619–0037, on the 

elevator bearing assembly link arm following 

section 5. Instructions, including all 

subsections, of Quest Aircraft Field Service 

Instruction, Yoke Anti-Rotation Guide Wear 

Pad Upgrade, Report No. FSI–108, Revision 

00, not dated, as specified in Quest Aircraft 

KODIAK 100 Recommended Service Bulletin 

SB15–01, dated March 26, 2015. Installing all 

four wear pads on the pilot and co-pilot arms 

of the elevator bearing assemblies terminates 

the repetitive inspections required in 

paragraph (g) of this AD. 

(j) 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 (k) 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. 

(k) Related Information 

For more information about this AD, 

contact David Herron, Aerospace Engineer, 

Seattle ACO, FAA, 1601 Lind Avenue SW., 

Renton, Washington 98057; phone: (425) 

917–6469; fax: (425) 917–6591; email: 

david.herron@faa.gov. 

(l) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

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

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Quest Aircraft Company KODIAK 100 

Mandatory Service Bulletin SB14–07, 

Revision 01, dated November 23, 2015. 

(ii) Quest Aircraft KODIAK Mandatory 

Service Bulletin SB14–07, dated August 26, 

2014. 

(iii) Quest Aircraft Company Field Service 

Instruction, Elevator Control System— 

Cushion Edging Inspection, Report No. FSI– 

105, Revision 00, not dated. 

(iv) Quest Aircraft KODIAK 100 

Recommended Service Bulletin SB15–01, 

dated March 26, 2015. 

(v) Quest Aircraft Field Service Instruction, 

Yoke Anti-Rotation Guide Wear Pad 

Upgrade, Report No. FSI–108, Revision 00, 

not dated. 

(3) For Quest Aircraft Design, LLC service 

information identified in this AD, contact 

Quest Aircraft Design, LLC, 1200 Turbine 

Drive, Sandpoint, Idaho 83864; telephone: 

(208) 263–1111; toll free: (866) 263–1112; 

email: CustomerService@QuestAircraft.com; 

Internet: www.questaircraft.com. 

(4) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call 816–329–4148. In 

addition, you can access this service 

information on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2015–5318. 

(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 Kansas City, Missouri, on March 

10, 2016. 

Pat Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–05898 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–2016–4227; Directorate 

Identifier 2016–NM–025–AD; Amendment 

39–18439; AD 2016–06–08] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 


asabaliauskas on DSK3SPTVN1PROD with RULES
Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 14705 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for The 

Boeing Company Model 787–8 and 787– 

9 airplanes powered by GE GEnx 

engines. This AD requires revising the 

airplane flight manual to provide the 

flight crew a new fan ice removal 

procedure to reduce the likelihood of 

engine damage due to fan ice shedding. 

This AD also requires, for certain 

airplanes, reworking the fan stator 

module assembly on GE GEnx–1B 

Performance Improvement Program 

(PIP) 2 engines. This AD was prompted 

by a recent engine fan blade rub event 

that caused an in-flight non-restartable 

power loss. We are issuing this AD to 

prevent reduced fan tip clearance, 

which could result in engine damage 

and a possible in-flight non-restartable 

power loss of one or both engines. 

DATES: This AD is effective March 18, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 18, 2016. 

We must receive comments on this 

AD by May 2, 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: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this final rule, contact General Electric 

Company, GE Aviation, Room 285, 1 

Neumann Way, Cincinnati, OH 45215; 

phone: 513–552–3272; email: geae.aoc@

ge.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–2016– 

4227. 

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–2016– 

4227; 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 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: Sue 

Lucier, Aerospace Engineer, Propulsion 

Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 

Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6438; fax: 425– 

917–6590; email: Suzanne.Lucier@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report of a significant 

GE GEnx–1B PIP2 engine fan rub event, 

apparently caused by partial fan ice 

shedding and a resulting fan imbalance 

that in turn caused substantial damage 

to the engine and an in-flight nonrestartable power loss. We continue to 

investigate this issue with Boeing and 

GE; however, the engine damage 

appears to be a result of reduced fan tip 

clearances common to the GEnx–1B 

PIP2 engine. The other engine on the 

event airplane was a GEnx–1B PIP1 

configuration that incurred expected 

wear and minor damage during the icing 

event and continued to operate 

normally. The event occurred in icing 

conditions at an altitude of 20,000 feet. 

Reduced fan tip clearance, if not 

corrected, could result in engine damage 

and a possible in-flight non-restartable 

power loss of one or both engines. We 

are issuing this AD to correct the unsafe 

condition on these products. 

Related Service Information Under 

1 CFR Part 51 

We reviewed GE GEnx–1B Service 

Bulletin 72–0309 R00, dated March 11, 

2016, which describes procedures for 

reworking the fan stator module 

assembly on GEnx–1B PIP2 engines. 

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. 

FAA’s Determination 

We are issuing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the GE service 

information described previously. This 

AD also requires revising the airplane 

flight manual (AFM) to provide the 

flight crew a new fan ice removal 

procedure to reduce the likelihood of 

engine damage due to fan ice shedding. 

Interim Action 

We consider this AD interim action. 

The engine manufacturer is currently 

developing a modification that will 

address the unsafe condition identified 

in this AD. Once this modification is 

developed, approved, and available, we 

may consider additional rulemaking. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because reduced fan tip clearance 

could result in engine damage and a 

possible in-flight non-restartable power 

loss of one or both engines. Therefore, 

we find that notice and opportunity for 

prior public comment are impracticable 

and that good cause exists for making 

this amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2016–4227 and Directorate 

Identifier 2016–NM–025–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 


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14706 Federal Register / Vol. 81, No. 53 / Friday, March 18, 2016 / Rules and Regulations 

Costs of Compliance 

We estimate that this AD affects 34 

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 

AFM revision .............. 1 work-hour × $85 per hour = $85 ........... $0 $85 $2,890. 

Rework ....................... 40 work-hours × $85 per hour = $3,400 .. 0 3,400 3,400 (1 affected airplane). 

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): 

2016–06–08 The Boeing Company: 

Amendment 39–18439; Docket No. 

FAA–2016–4227; Directorate Identifier 

2016–NM–025–AD. 

(a) Effective Date 

This AD is effective March 18, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 787–8 and 787–9 airplanes, 

certificated in any category, powered by 

General Electric (GE) GEnx engines. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 72, Engines. 

(e) Unsafe Condition 

This AD was prompted by a recent engine 

fan blade rub event that caused an in-flight 

non-restartable power loss. We are issuing 

this AD to prevent reduced fan tip clearance, 

which could result in engine damage and a 

possible in-flight non-restartable power loss 

of one or both engines. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Revision of Airplane Flight Manual 

(AFM): Certificate Limitations 

Within 7 days after the effective date of 

this AD, revise the Certificate Limitations 

chapter of the applicable Boeing 787 AFM to 

include the statement provided in figure 1 to 

paragraph (g) of this AD. This may be done 

by inserting a copy of this AD into the AFM. 

FIGURE 1 TO PARAGRAPH (g) OF THIS

AD 

Engine Operational Limits 

Cold Weather Operations Fan Ice Removal 

In order to avoid possible fan damage and 

engine failure, when in icing conditions 

above 12,500 feet MSL, the flight crew 

must comply with the Cold Weather Operations Additional Fan Ice Removal procedure contained in the Operating Procedures chapter of this manual. 

(h) AFM Revision: Operating Procedures 

Within 7 days after the effective date of 

this AD, revise the Operating Procedures 

chapter of the Boeing 787 AFM to include the 

statement provided in figure 2 to paragraph 

(h) of this AD. This may be done by inserting 

a copy of this AD into the AFM. 

FIGURE 2 TO PARAGRAPH (h) OF THIS

AD 

Cold Weather Operations 

Additional Fan Ice Removal Procedure 

This procedure is required when in icing conditions above 12,500 feet MSL, by the Engine Operational Limits Cold Weather Operations Fan Ice Removal limitation contained in the Certificate Limitations chapter 

of this manual. The language below shall 

not be modified. 

During flight in icing conditions (EAI EICAS 

indication showing) with N1 settings below 

85%, or when fan icing is suspected due to 

high engine vibration, the fan blades must 

be cleared of any ice. Do the following procedure every 5 minutes on both engines, 

one engine at a time: Increase to a minimum of 85% N1 momentarily, then resume normal operation. 

(i) Rework 

For airplanes with two engines with engine 

serial numbers listed in paragraph 1.A., 

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

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

On or before March 25, 2016, rework the fan 

stator module assembly of one of the engines, 

in accordance with paragraphs 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. 

(j) Parts Installation Limitation 

As of March 25, 2016, no person may 

operate an airplane that has two engines with 

engine serial numbers listed in paragraph 


asabaliauskas on DSK3SPTVN1PROD with RULES
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 


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