Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26109 

(3) For Piper Aircraft, Inc. service 

information identified in this AD, contact 

Piper Aircraft, Inc., 926 Piper Drive, Vero 

Beach, Florida 32960; telephone: (772) 567– 

4361; fax: (772) 978–6573; Internet: 

www.piper.com/home/pages/

Publications.cfm. 

(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. 

(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 April 

14, 2016. 

Robert P. Busto, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–09238 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1428; Directorate 

Identifier 2015–NM–026–AD; Amendment 

39–18499; AD 2016–09–01] 

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 777–200 

and –300 series airplanes. This AD was 

prompted by reports of fatigue cracking 

of a certain chord of the pivot bulkhead. 

This AD requires repetitive inspections 

for cracking of the left side and right 

side forward outer chords of the pivot 

bulkhead, and related investigative and 

corrective actions if necessary. This AD 

also provides a modification of the pivot 

bulkhead, which would terminate the 

repetitive inspections. We are issuing 

this AD to detect and correct fatigue 

cracking of the outer flanges of the left 

and right side forward outer chords of 

the pivot bulkhead, which could result 

in a severed forward outer chord and 

consequent loss of horizontal stabilizer 

control. 

DATES: This AD is effective June 6, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of June 6, 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– 

1428. 

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– 

1428; 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: 

Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6513; 

fax: 425–917–6590; email: 

narinder.luthra@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 777–200 and –300 series 

airplanes. The NPRM published in the 

Federal Register on June 15, 2015 (80 

FR 34103) (‘‘the NPRM’’). The NPRM 

was prompted by reports of fatigue 

cracking of a certain chord of the pivot 

bulkhead. The NPRM proposed to 

require repetitive inspections for 

cracking of the left side and right side 

forward outer chords of the pivot 

bulkhead, and related investigative and 

corrective actions if necessary. The 

NPRM also proposed to provide a 

modification of the pivot bulkhead, 

which would terminate the repetitive 

inspections. We are issuing this AD to 

detect and correct fatigue cracking of the 

outer flanges of the left and right side 

forward outer chords of the pivot 

bulkhead, which could result in a 

severed forward outer chord and 

consequent loss of horizontal stabilizer 

control. 

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 To Exclude Certain 

Requirements From the NPRM 

American Airlines (AA) requested 

that we revise the NPRM to exclude 

doing the work in accordance with 

paragraph 3.B.4., of the Work 

Instructions of Boeing Alert Service 

Bulletin 777–53A0075, dated January 

14, 2015, which specifies ‘‘Put the 

airplane back into a serviceable 

condition.’’ AA stated that doing this 

action does not affect the condition that 

the AD seeks to address. AA added that 

most operators will accomplish these 

modifications as part of a maintenance 

visit, and returning the airplane to a 

serviceable condition will not be 

possible in the context of the statement, 

but rather will occur at a point in time 

well after the work is completed. 

We agree that putting the airplane 

back into a serviceable condition is not 

directly related to addressing the unsafe 

condition identified in this AD. 

However, we do not agree to specifically 

exclude paragraph 3.B.4., of the Work 

Instructions of Boeing Alert Service 

Bulletin 777–53A0075, dated January 

14, 2015, from this final rule because it 

is not required for compliance with the 

AD actions. 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee (AD ARC), to 

enhance the AD system. One 

enhancement is a new process for 

annotating which steps in the service 

information are ‘‘required for 

compliance’’ (RC) with an AD. 

Differentiating these steps from other 

tasks in the service information is 

expected to improve an owner’s/

operator’s understanding of AD 

requirements and help provide 

consistent judgment in AD compliance. 

In response to the AD Implementation 

ARC, the FAA released AC 20–176A, 

dated June 16, 2014 (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/rg

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26110 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

AdvisoryCircular.nsf/0/979ddd

1479e1ec6f86257cfc0052d4e9/$FILE/

AC%2020-176A.pdf); and Order 

8110.117A, dated June 18, 2014 (http:// 

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgOrders.nsf/0/

d715cdfc08ac0ddc86257cfc00528297/

$FILE/110.117A.pdf), which include the 

concept of RC. The FAA has begun 

implementing this concept in ADs when 

we receive service information 

containing RC steps. 

Boeing Alert Service Bulletin 777– 

53A0075, dated January 14, 2015, 

includes the concept of RC. In 

paragraph 3.B. of the Work Instructions 

of Boeing Alert Service Bulletin 777– 

53A0075, dated January 14, 2015, 

certain steps are marked RC. The step 

that specifies ‘‘Put the airplane back 

into a serviceable condition’’ is not 

marked RC. Therefore, no change to this 

final rule is necessary in this regard. 

Request To Change Certain Language in 

the NPRM 

Boeing and United Airlines (UA) 

asked that the language in paragraph (h) 

of the proposed AD be reworded for 

clarity. Boeing asked that we account for 

the small crack repair being performed 

on one side only. UA stated that as 

written, inspecting the left side and 

right side forward outer chords is 

incorrect since the small crack repair is 

performed on one side only. UA noted 

that the small crack repair may be 

accomplished on one side of the 

airplane only, depending on inspection 

findings. UA asked that paragraph (h) of 

the proposed AD be changed to specify 

‘‘. . . do a surface high frequency eddy 

current (HFEC) inspection, an open-hole 

HFEC inspection, and a detailed 

inspection for cracking of the repaired 

side (left, right, or both) forward outer 

chords of the STA 2370 pivot 

bulkhead.’’ Boeing recommended that 

the language be reworded to specify an 

‘‘. . . inspection for cracking of the 

repaired forward outer chords . . .’’ 

We agree with the commenters’ 

requests for the reasons provided. We 

have changed the language in paragraph 

(h) of this AD to specify ‘‘. . . do a 

surface HFEC inspection, an open-hole 

HFEC inspection, and a detailed 

inspection for cracking of the repaired 

side forward outer chords of the STA 

2370 pivot bulkhead.’’ 

Boeing and UA asked that the 

language in paragraph (i) of the 

proposed AD be reworded for clarity. 

Boeing asked that we account for the 

scenario where the small crack repair is 

performed on one side only. Boeing 

stated that the terminating actions for 

each side of the bulkhead are 

independent of each other. UA stated 

that using ‘‘and’’ is incorrect because 

the modification can only be 

accomplished on one side, not both the 

left and right sides, depending on 

inspection findings. 

We agree with the commenters for the 

reasons provided. We have changed the 

language in paragraph (i) of this AD 

accordingly. 

Request To Include Revised Service 

Information 

All Nippon Airways (ANA) stated that 

Boeing Alert Service Bulletin 777– 

53A0075, dated January 14, 2015; and 

Boeing Service Bulletin 777–53–0076, 

dated January 14, 2015; contain many 

inconsistencies. We infer that ANA is 

requesting that we include revised 

service information because there are 

errors in the original issues. 

We agree with the commenter. Boeing 

has issued Boeing Alert Service Bulletin 

777–53A0075, Revision 1, dated 

December 14, 2015; and Boeing Service 

Bulletin 777–53–0076, Revision 1, dated 

December 21, 2015; which include 

changes found during validation and 

clarify and correct issues identified by 

operators. We have included the revised 

service information as the appropriate 

source of service information for 

accomplishing the actions required by 

this AD and we have referred to Boeing 

Alert Service Bulletin 777–53A0075, 

Revision 1, dated December 14, 2015, in 

the applicability in paragraph (c) of this 

AD. We have also added a new credit 

paragraph (k) to this AD for using the 

original issues of the service 

information and reidentified subsequent 

paragraphs accordingly. 

Request To Add a New Paragraph for 

Clarification 

Boeing asked that we add a new 

paragraph (j)(3) to the proposed AD to 

specify the following: 

If conducting the Part 2 Small Crack Repair 

of the Service Bulletin 777–53A0075 dated 

January 14, 2015, verify the fastener heads 

and nuts will not interfere with the fillet 

radius of the parts in the repair installation. 

If interference will occur, repair before 

further flight using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. . . 

Boeing also asked that we add a 

reference to paragraph (j)(3) in 

paragraph (g) of the proposed AD by 

including it in the exception sentence. 

Boeing stated that during a recent 

validation it was discovered that, in 

some cases, radius fillers are required to 

prevent fasteners from riding the fillet 

radius of the extended splice chord used 

in the small crack repair specified in 

Part 2 of Boeing Alert Service Bulletin 

777–53A0075, dated January 14, 2015. 

We agree with the commenter that 

interference between the fastener and 

fillet case should be minimized; 

however, we do not agree to add a new 

paragraph (j)(3) to this AD. Boeing has 

issued Boeing Alert Service Bulletin 

777–53A0075, Revision 1, dated 

December 14, 2015, which includes 

instructions for accomplishing the small 

crack repair. As stated previously, we 

have revised this AD to refer to Boeing 

Alert Service Bulletin 777–53A0075, 

Revision 1, dated December 14, 2015, 

for accomplishing certain actions 

required by this AD. 

Request To Correct Minor Error 

Boeing asked that we change the 

service information number identified 

in paragraph (j)(2) of the proposed AD 

from ‘‘777–530076’’ to ‘‘777–53–0076.’’ 

We agree that the hyphen is missing 

from the service information number. 

We have included the hyphen in the 

service information number identified 

in paragraph (j)(2) of this AD 

accordingly. 

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 changes described previously 

and 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. 

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 information. 

• Boeing Alert Service Bulletin 777– 

53A0075, Revision 1, dated December 

14, 2015. This service information 

describes procedures for repetitive 

detailed and HFEC inspections for 

cracking of the outer flanges of the left 

and right side forward outer chords of 

the STA 2370 pivot bulkhead, repetitive 

post-repair inspections for certain 

airplanes, and related investigative and 

corrective actions. 

• Boeing Service Bulletin 777–53– 

0076, Revision 1, dated December 21, 

2015. This service information describes 

procedures for a modification of the 

STA 2370 pivot bulkhead by replacing 

the left and right side forward outer 

chords and upper splice angles, and 

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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 26111 

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 60 

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 of left and right 

side pivot bulkhead forward chord.

Up to 15 work-hours × $85 per hour = $1,275 per inspection cycle.$0 Up to $1,275 per 

inspection cycle.

Up to $76,500 per inspection cycle. 

Post-repair Inspections ........ Up to 11 work-hours × $85 per hour = $935 per inspection cycle.0 Up to $935 per inspection cycle.Up to $56,100 per inspection cycle. 

We estimate the following costs to do 

any necessary repairs and modifications 

that would be required based on the 

results of the inspection. We have no 

way of determining the number of 

airplanes that might need these actions. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Small crack repair ........................ Up to 45 work-hours × $85 per hour = $3,825 per side ................... 1 Up to $7,650. 

Modification of the STA 2370 

Pivot Bulkhead (forward outer 

chord replacement).

Up to 137 work-hours × $85 per hour = $11,645 ............................. $34,086 Up to $45,731. 

1We have received no definitive data that would enable us to provide parts cost estimates for the on-condition repair specified in this AD. 

According to the manufacturer, some 

of the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

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): 

2016–09–01 The Boeing Company: 

Amendment 39–18499; Docket No. 

FAA–2015–1428; Directorate Identifier 

2015–NM–026–AD. 

(a) Effective Date 

This AD is effective June 6, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 777–200 and –300 series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 777–53A0075, 

Revision 1, dated December 14, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fatigue cracking of the forward outer chord of 

the station (STA) 2370 pivot bulkhead. We 

are issuing this AD to detect and correct 

fatigue cracking of the outer flanges of the left 

and right side forward outer chords of the 

STA 2370 pivot bulkhead, which could result 

in a severed forward outer chord and 

consequent loss of horizontal stabilizer 

control. 

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26112 Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions 

At the times specified in table 1 of 

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

Alert Service Bulletin 777–53A0075, 

Revision 1, dated December 14, 2015, except 

as provided in paragraph (j)(1) of this AD: Do 

a detailed inspection and high frequency 

eddy current (HFEC) inspections for cracking 

of the left and right side forward outer chords 

of the STA 2370 pivot bulkhead, and do all 

applicable related investigative and 

corrective actions, in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0075, Revision 1, 

dated December 14, 2015, except as provided 

in paragraph (j)(2) of this AD. Do all 

applicable related investigative and 

corrective actions before further flight. 

Repeat the inspections thereafter at the 

applicable intervals specified in table 1 of 

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

Alert Service Bulletin 777–53A0075, 

Revision 1, dated December 14, 2015, until 

the modification specified in paragraph (i) of 

this AD is done. 

(h) Post-Repair Inspections 

For airplanes on which any repair 

specified in Part 2 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

777–53A0075 has been done: At the times 

specified in table 2 of paragraph 1.E., 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 777–53A0075, Revision 1, dated 

December 14, 2015, do a surface HFEC 

inspection, an open-hole HFEC inspection, 

and a detailed inspection for cracking of the 

repaired side forward outer chords of the 

STA 2370 pivot bulkhead, and do all 

applicable related investigative and 

corrective actions, in accordance with Part 3 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 777–53A0075, 

Revision 1, dated December 14, 2015, except 

as required by paragraph (j)(2) of this AD. Do 

all applicable related investigative and 

corrective actions before further flight. 

Repeat the inspections thereafter at the 

applicable times specified in table 2 of 

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

Alert Service Bulletin 777–53A0075, 

Revision 1, dated December 14, 2015, until 

the modification specified in paragraph (i) of 

this AD is done. 

(i) Terminating Action 

Modifying the STA 2370 pivot bulkhead by 

replacing the left or right side forward outer 

chords and upper splice angles, and doing all 

applicable related investigative and 

corrective actions, terminates the repetitive 

inspections required by paragraphs (g) and 

(h) of this AD, for the modified location only. 

The modification must be done in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 777– 

53–0076, Revision 1, dated December 21, 

2015, except as required by paragraph (j)(2) 

of this AD. 

(j) Exceptions to Service Bulletin 

Specifications 

(1) Where Boeing Alert Service Bulletin 

777–53A0075, Revision 1, dated December 

14, 2015, specifies a compliance time ‘‘after 

the Original Issue date of this Service 

Bulletin,’’ this AD requires compliance 

within the specified compliance time after 

the effective date of this AD. 

(2) Although Boeing Alert Service Bulletin 

777–53A0075, Revision 1, dated December 

14, 2015; and Boeing Service Bulletin 777– 

53–0076, Revision 1, dated December 21, 

2015; specify to contact Boeing for 

appropriate action, and Boeing Alert Service 

Bulletin 777–53A0075, Revision 1, dated 

December 14, 2015, specifies that action as 

‘‘RC’’ (Required for Compliance), this AD 

requires repair before further flight using a 

method approved in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(k) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions required by paragraphs (g) and (h) of 

this AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin 777–53A0075, 

dated January 14, 2015. 

(2) This paragraph provides credit for the 

actions required by paragraph (i) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Service 

Bulletin 777–53–0076, dated January 14, 

2015. 

(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)(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) Except as required by paragraph (j)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (l)(4)(i) and (l)(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. 

(m) Related Information 

(1) For more information about this AD, 

contact Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6513; fax: 425– 

917–6590; email: narinder.luthra@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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) Boeing Alert Service Bulletin 777– 

53A0075, Revision 1, dated December 14, 

2015. 

(ii) Boeing Service Bulletin 777–53–0076, 

Revision 1, dated December 21, 2015. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone: 206– 

544–5000, extension 1; fax: 206–766–5680; 

Internet: https://www.myboeingfleet.com. 

(4) You may view this service information 

at 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 April 14, 

2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–09650 Filed 4–29–16; 8:45 am] 

BILLING CODE 4910–13–P 

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