21716 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 

Worth, TX 76177; telephone (817) 222–5110; 

email 9-ASW-FTW-AMOC-Requests@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(g) Additional Information 

(1) Airbus Helicopters Alert Service 

Bulletin ASB No. SA341/SA342–05.40, 

Revision 0, dated April 28, 2014, which is 

not incorporated by reference, contains 

additional information about the subject of 

this final rule. For Airbus Helicopters service 

information identified in this final rule, 

contact Airbus Helicopters, 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http:// 

www.airbushelicopters.com/techpub. You 

may review a copy of the service information 

at the FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy, 

Room 6N–321, Fort Worth, TX 76177. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2014–0216, dated September 24, 2014. 

You may view the EASA AD on the Internet 

at http://www.regulations.gov in Docket No. 

FAA–2015–5914. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6700, Main Rotor. 

(i) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 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) Gazelle Inspection—Check 65.12.607, 

‘‘Main Rotor Head: Torsion Tie-Back Check 

(Post MOD 076171),’’ dated August 2008, of 

the Eurocopter Gazelle Helicopter 

Maintenance Manual, Tome 1. 

(ii) Reserved. 

(3) For Eurocopter service information 

identified in this final rule, contact Airbus 

Helicopters, 2701 N. Forum Drive, Grand 

Prairie, TX 75052; telephone (972) 641–0000 

or (800) 232–0323; fax (972) 641–3775; or at 

http://www.airbushelicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 10101 Hillwood Pkwy, 

Room 6N–321, Fort Worth, TX 76177. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on March 31, 

2016. 

James A. Grigg, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–07979 Filed 4–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3147; Directorate 

Identifier 2014–NM–094–AD; Amendment 

39–18479; AD 2016–08–03] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for all The 

Boeing Company Model 777–200, 

–200LR, –300, and –300ER series 

airplanes. This AD was prompted by 

reports of fractured forward attach 

fittings of the inboard flap outboard aft 

flap track. The fractured fittings were 

determined to be the result of corrosion 

pits forming on the inside diameter of 

the fittings. This AD requires an 

inspection for the affected part number 

and serial number of the main flap; 

various additional repetitive inspections 

of the fitting, if necessary; and 

replacement of the fitting or nested 

bushing installation, if necessary, which 

would terminate the inspections. This 

AD also provides an optional 

terminating action for the repetitive 

inspections. We are issuing this AD to 

detect and correct fracture of the fitting, 

which could result in the loss of the 

inboard aft flap and could lead to a 

punctured fuselage, causing injury to 

the flightcrew and passengers, and 

damage to the airplane. 

DATES: This AD is effective May 18, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 18, 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– 

3147. 

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– 

3147; 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: Eric 

Lin, Aerospace Engineer, Airframe 

Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: 425–917–6412; fax: 425– 

917–6590; email: Eric.Lin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to all The Boeing Company Model 

777–200, –200LR, –300, and –300ER 

series airplanes. The NPRM published 

in the Federal Register on August 25, 

2015 (80 FR 51491) (‘‘the NPRM’’). The 

NPRM was prompted by reports of 

fractured forward attach fittings of the 

inboard flap outboard aft flap track. The 

fractured fittings were determined to be 

the result of corrosion pits forming on 

the inside diameter of the fittings. The 

NPRM proposed to require an 

inspection for the affected part number 

and serial number of the main flap; 

various additional repetitive inspections 

of the fitting, if necessary; and 

replacement of the fitting or nested 

bushing installation, if necessary, which 

would terminate the inspections. The 

proposed AD also provided an optional 

terminating action for the repetitive 

inspections. We are issuing this AD to 

detect and correct fracture of the fitting, 

which could result in the loss of the 

inboard aft flap and could lead to a 

punctured fuselage, causing injury to 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 21717 

the flightcrew and passengers, and 

damage to 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. Benjamin 

Kerensa commented that he supports 

the NPRM. 

Request To Change Terminology 

Boeing requested that we change the 

phrase ‘‘inboard flap of the main flap’’ 

to ‘‘main flap of the inboard flap 

assembly’’ in paragraphs (g) and (h) of 

the proposed AD. Boeing stated that this 

would clarify the inspection location. 

We agree with the commenter’s 

request for the reason provided by the 

commenter. We have revised paragraphs 

(g) and (h) of this AD accordingly. 

Request To Clarify Requirements of a 

Certain Terminating Action 

Boeing requested that we revise the 

terminating action specified in 

paragraph (k)(1) of the proposed AD. 

Boeing recommended that at the end of 

paragraph (k)(1) of the proposed AD, we 

add the following language, ‘‘Prior to 

accomplishing this option, the 

inspections of paragraph (h) must be 

accomplished and no cracking must 

have been found during that 

inspection.’’ Boeing commented that the 

bushing replacement is only a 

terminating action if the fitting has been 

verified to be crack free. 

We agree to clarify the terminating 

action. As specified in Boeing Special 

Attention Service Bulletin 777–57– 

0094, Revision 1, dated November 5, 

2014, if cracking is found during an 

inspection that is part of the terminating 

action, a fitting replacement must be 

done instead of the terminating action. 

In addition, Boeing Special Attention 

Service Bulletin 777–57–0094, Revision 

1, dated November 5, 2014, specifies 

that if corrosion cannot be removed 

during the terminating action, a fitting 

replacement must be done instead of the 

terminating action. 

Therefore, we have revised paragraph 

(k)(1) of this AD to specify that the 

terminating action is acceptable 

provided no cracking is found during 

any inspection specified in Part 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777– 

57–0094, Revision 1, dated November 5, 

2014, and all corrosion has been 

removed. 

We have also clarified the terminating 

actions specified in paragraphs (h), (i), 

(j), (k)(1), (k)(2), and (k)(3) of this AD to 

specify the terminating actions apply 

only to that fitting on which the 

terminating action is done. 

In addition, we have clarified the 

actions specified in paragraphs (i)(3)(i), 

(i)(3)(ii), and (i)(3)(iii) of this AD by 

specifying the actions include doing all 

applicable related investigative actions. 

Also, we have clarified the actions 

specified in paragraphs (j)(1) and (j)(2) 

of this AD by specifying the actions 

include doing all applicable related 

investigative and corrective actions. 

Request To Clarify Terminating Action 

Is an Option to the Inspections 

Boeing and American Airlines (AA) 

requested that we clarify that the 

terminating action can be done instead 

of the inspections. AA commented to 

revise the terminating action paragraph 

to state the following: 

If any inboard flap of the main flap having 

an affected part number and serial number is 

found during the inspection required by 

paragraph (g) of this AD: Except as provided 

by paragraph (l) of this AD, at the applicable 

time specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 777–57–0094, Revision 1, 

dated November 5, 2014, do the terminating 

action in paragraph (k)(1), (k)(2), or (k)(3) of 

this AD or do the inspections specified in 

paragraph (h)(1) or (h)(2) of this AD, in 

accordance with the Accomplishment 

Instructions of Boeing Special attention 

Service Bulletin 777–57–0094, Revision 1, 

dated November 5, 2014. Repeat the 

inspections thereafter at the applicable times 

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

Boeing Special Attention Service Bulletin 

777–57–0094, Revision 1, dated November 5, 

2014, until a terminating action in paragraph 

(k)(1), (k)(2), or (k)(3) of this AD is done. 

AA commented that this change 

would align the proposed rule with 

paragraph 1.E., ‘‘Compliance,’’ table 1 

and table 2, of Boeing Special Attention 

Service Bulletin 777–57–0094, Revision 

1, dated November 5, 2014. AA also 

stated that this would clearly indicate 

that the terminating action would 

preclude having to accomplish first the 

initial inspection requirement in 

paragraph (h) of the proposed AD. 

Boeing requested that we add a sentence 

to the end of paragraph (h) to specify 

that the inspections are not required for 

any affected inboard flap assembly 

where one of the terminating actions 

specified in paragraph (k)(1), (k)(2), or 

(k)(3) of the proposed AD have been 

done. 

We agree with the commenters’ 

request. We have revised paragraph (h) 

of this AD to clarify that the terminating 

actions may preclude the initial 

inspections because rework or 

replacement of the parts prevent the 

unsafe condition. 

Request To Clarify the Applicability 

Delta Airlines (DAL) requested that 

we clarify whether paragraph (c) of the 

proposed AD is intended for all Model 

777–200, –200LR, –300, and –300ER 

series airplanes, or all Model 777–200, 

–200LR, –300 and –300ER series 

airplanes, identified as Groups 1, 2, and 

4 airplanes in Boeing Special Attention 

Service Bulletin 777–57–0094, Revision 

1, dated November 5, 2014. 

DAL stated that paragraph (c) of the 

proposed AD does not contain Boeing 

Special Attention Service Bulletin 777– 

57–0094, Revision 1, dated November 5, 

2014, to identify the airplane’s 

applicability for the proposed AD. DAL 

commented that in the proposed rule 

under ‘‘Differences Between This 

Proposed AD and the Service 

Information,’’ the airplane’s 

applicability is stated. DAL also stated 

that the same paragraph states that the 

proposed AD is applicable only to 

Groups 1, 2, and 4 airplanes (Model 

777–200, –200LR, –300 and –300ER 

series airplanes) specified in Boeing 

Service Bulletin 777–57–0094, Revision 

1, dated November 5, 2014. DAL 

commented that a review of the 

‘‘Compliance’’ paragraph in the service 

information indicates that the FAA will 

possibly release an AD for airplanes in 

Groups 1, 2, and 4. 

We agree with the commenter’s 

request to clarify the applicability of 

this AD. This AD applies to all Model 

777–200, –200LR, –300, and –300ER 

series airplanes as specified in 

paragraph (c) of this AD. The 

description of Groups 1, 2, and 4 

airplanes in section 1.A., ‘‘Effectivity,’’ 

of Boeing Special Attention Service 

Bulletin 777–57–0094, Revision 1, dated 

November 5, 2014, specifies Model 777– 

200, –200LR, –300, and –300ER series 

airplanes. Additionally, as noted in the 

service information, the table of variable 

numbers given in section 1.A., 

‘‘Effectivity,’’ only reflects up to line 

number 1322, and affected airplanes 

after line number 1322 will be added to 

the profile page of MyBoeingFleet.com. 

Therefore, this AD applies to all Model 

777–200, –200LR, –300, and –300ER 

series airplanes. We have not changed 

this AD in this regard. 

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: 


jstallworth on DSK7TPTVN1PROD with RULES
21718 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 

• 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 Boeing Special 

Attention Service Bulletin 777–57– 

0094, Revision 1, dated November 5, 

2014. The service information describes 

procedures for an inspection for the 

affected part number and serial number 

of the main flap; various additional 

repetitive inspections of the fitting, if 

necessary; and replacement of the fitting 

or nested bushing installation, if 

necessary, which would terminate the 

inspections. The service information 

also describes an optional terminating 

action for the repetitive inspections. 

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 148 

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 

Inspection to determine the part 

number.

3 work-hours × $85 per hour = $255 $0 $255 .............................. $37,740. 

Additional Inspections ....................... Up to 7 work-hours × $85 per hour = 

$595, per cycle.

0 Up to $595, per cycle ... Up to $88,060, per 

cycle. 

We estimate the following costs to do 

any necessary replacements that will be 

required based on the results of the 

inspection. The nested bushing 

installation of the attach fitting and the 

fitting replacement are also optional 

terminating actions. We have no way of 

determining the number of aircraft on 

which these actions might be done. 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Nested bushing installation of the attach fitting ........... 40 work-hours × $85 per hour = $3,400 ..................... $45 $3,445. 

Fitting replacement ...................................................... 73 work-hours × $85 per hour = $6,205 ..................... 7,400 13,605. 

According to the manufacturer, all 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): 

2016–08–03 The Boeing Company: 

Amendment 39–18479; Docket No. 

FAA–2015–3147; Directorate Identifier 

2014–NM–094–AD. 

(a) Effective Date 

This AD is effective May 18, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 777–200, –200LR, –300, and 

–300ER series airplanes, certificated in any 

category. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 21719 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Unsafe Condition 

This AD was prompted by reports of 

fractured forward attach fittings of the 

inboard flap outboard aft flap track. The 

fractured fittings were determined to be the 

result of corrosion pits forming on the inside 

diameter of the fittings. We are issuing this 

AD to detect and correct fracture of the 

fitting, which could result in the loss of the 

inboard aft flap and could lead to a 

punctured fuselage, causing injury to the 

flightcrew and passengers, and damage to the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection To Determine the Part Number 

At the applicable time specified in 

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

Special Attention Service Bulletin 777–57– 

0094, Revision 1, dated November 5, 2014, 

except as provided by paragraph (l) of this 

AD: Do an inspection of the main flap of the 

inboard flap assembly for affected part and 

serial numbers, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–57– 

0094, Revision 1, dated November 5, 2014. A 

review of airplane maintenance records is 

acceptable in lieu of this inspection if the 

part number and serial number of the inboard 

flap can be conclusively determined from 

that review. 

(h) Additional Inspections 

If any main flap of the inboard flap 

assembly having an affected part number and 

serial number is found during the inspection 

required by paragraph (g) of this AD: Except 

as provided by paragraph (l) of this AD, at 

the applicable time specified in paragraph 

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

Attention Service Bulletin 777–57–0094, 

Revision 1, dated November 5, 2014, do the 

terminating action specified in paragraph 

(k)(1), (k)(2), or (k)(3) of this AD, or do the 

inspections specified in paragraph (h)(1) or 

(h)(2) of this AD, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–57– 

0094, Revision 1, dated November 5, 2014. 

Repeat the inspections thereafter at the 

applicable times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 777–57–0094, Revision 1, 

dated November 5, 2014, until a terminating 

action in paragraph (k)(1), (k)(2), or (k)(3) of 

this AD is done. Accomplishing a 

terminating action specified in paragraph 

(k)(1), (k)(2), or (k)(3) of this AD terminates 

the inspections required by this paragraph for 

that fitting only. 

(1) At the forward attach fitting of the aft 

flap track of the inboard flap: Do a detailed 

inspection for cracking and bushing 

migration, and a high frequency eddy current 

inspection for cracking, in accordance with 

Part 2 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–57–0094, Revision 1, dated November 5, 

2014. 

(2) At the forward attach fitting of the aft 

flap track of the inboard flap: Do a detailed 

inspection for cracking and bushing 

migration, and an ultrasound inspection for 

cracking, in accordance with Part 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–57– 

0094, Revision 1, dated November 5, 2014. 

(i) Corrective Action for Bushing Migration 

If any bushing migration but no cracking is 

found during any inspection required by 

paragraph (h) of this AD: At the applicable 

times specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 777–57–0094, Revision 1, 

dated November 5, 2014, do the actions 

specified in paragraphs (i)(1) through (i)(3) of 

this AD. Accomplishment of a terminating 

action specified in paragraph (i)(3) or (k) of 

this AD terminates the actions required by 

this paragraph for that fitting only. 

(1) Apply corrosion inhibiting compound 

BMS 3–23, Type II, around the bushing 

flanges on each side of the fitting, in 

accordance with the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–57–0094, Revision 1, 

dated November 5, 2014. Re-apply the 

corrosion inhibiting compound at the time 

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

Boeing Special Attention Service Bulletin 

777–57–0094, Revision 1, dated November 5, 

2014. 

(2) Repeat the inspections specified in 

paragraph (h)(1) or (h)(2) of this AD, except 

inspect for cracking only. 

(3) Do a terminating action specified in 

paragraph (i)(3)(i), (i)(3)(ii), or (i)(3)(iii) of 

this AD. 

(i) Install a nested bushing to the forward 

attach fitting of the aft flap track of the 

inboard flap, including doing all applicable 

related investigative actions, in accordance 

with Part 4 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 777–57–0094, Revision 1, 

dated November 5, 2014. 

(ii) Replace the forward attach fitting of the 

aft flap track of the inboard flap with an 

aluminum fitting, including doing all 

applicable related investigative actions, in 

accordance with Part 5 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–57– 

0094, Revision 1, dated November 5, 2014. 

(iii) Replace the forward attach fitting of 

the aft flap track of the inboard flap with a 

titanium fitting, including doing all 

applicable related investigative actions, in 

accordance with Part 6 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–57– 

0094, Revision 1, dated November 5, 2014. 

(j) Corrective Actions for Cracking 

If any cracking is found during any 

inspection required by paragraph (h) or (i)(3) 

of this AD: At the applicable time specified 

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

Special Attention Service Bulletin 777–57– 

0094, Revision 1, dated November 5, 2014, 

do a terminating action specified in 

paragraph (j)(1) or (j)(2) of this AD. 

Replacement of the forward attach fitting as 

specified in paragraph (j)(1) or (j)(2) of this 

AD terminates the actions in this AD for that 

fitting only. 

(1) Replace the forward attach fitting of the 

aft flap track of the inboard flap with an 

aluminum fitting, including doing all 

applicable related investigative and 

corrective actions, in accordance with Part 5 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–57–0094, Revision 1, dated November 5, 

2014. 

(2) Replace the forward attach fitting of the 

aft flap track of the inboard flap with a 

titanium fitting, including doing all 

applicable related investigative and 

corrective actions, in accordance with Part 6 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–57–0094, Revision 1, dated November 5, 

2014. 

(k) Optional Terminating Actions 

(1) Installation of the nested bushing to the 

forward attach fitting of the aft flap track of 

the inboard flap, in accordance with Part 4 

of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–57–0094, Revision 1, dated November 5, 

2014, terminates the requirements of this AD 

for that fitting only, provided no cracking is 

found during any inspection specified in Part 

4 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–57–0094, Revision 1, dated November 5, 

2014, and all corrosion has been removed. 

(2) Replacement of the forward attach 

fitting of the aft flap track of the inboard flap 

with an aluminum fitting, in accordance with 

Part 5 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–57–0094, Revision 1, dated November 5, 

2014, terminates the requirements of this AD 

for that fitting only. 

(3) Replacement of the forward attach 

fitting of the aft flap track of the inboard flap 

with a titanium fitting, in accordance with 

Part 6 of the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–57–0094, Revision 1, dated November 5, 

2014, terminates the requirements of this AD 

for that fitting only. 

(l) Exception to the Service Information 

Where Boeing Special Attention Service 

Bulletin 777–57–0094, Revision 1, dated 

November 5, 2014, 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. 

(m) Credit for Previous Actions 

(1) This paragraph provides credit for the 

actions specified in paragraphs (h)(1) and 

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

performed before the effective date of this AD 

using Boeing Special Attention Service 

Bulletin 777–57–0094, dated January 29, 

2014, which is not incorporated by reference 

in this AD. 

(2) This paragraph provides credit for the 

actions specified in paragraph (h)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Multi Operator Message MOM–MOM–13– 


jstallworth on DSK7TPTVN1PROD with RULES
21720 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 

0137–01B, dated February 21, 2013, which is 

not incorporated by reference in this AD. 

(n) 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 (o)(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) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (n)(4)(i) and (n)(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. 

(o) Related Information 

(1) For more information about this AD, 

contact Eric Lin, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone: 425–917–6412; fax: 

425–917–6590; email: Eric.Lin@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(p) 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 Special Attention Service 

Bulletin 777–57–0094, Revision 1, dated 

November 5, 2014. 

(ii) Reserved. 

(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/ibr-locations.html. 

Issued in Renton, Washington, on March 

31, 2016. 

Victor Wicklund, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–08359 Filed 4–12–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–2959; Directorate 

Identifier 2015–NM–008–AD; Amendment 

39–18470; AD 2016–07–25] 

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 787–8 

airplanes. This AD was prompted by 

reports indicating that the ram air 

turbine (RAT) assembly may fail to 

operate if deployed at low airspeeds. 

This AD requires replacing either the 

RAT pump and control module 

assembly or the entire RAT assembly. 

We are issuing this AD to prevent 

failure of the RAT assembly to operate 

at low air speeds. The volume fuse on 

the RAT assembly may be activated inflight before the RAT is deployed. This 

may lead to improper pump hydraulic 

pressure offloading when the RAT is 

needed. Failure of the RAT to operate in 

an all engine out event would result in 

loss of control of the airplane. 

DATES: This AD is effective May 18, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of May 18, 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– 

2959. 

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– 

2959; 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: 

Sean J. Schauer, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office (ACO), 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425– 

917–6479; fax: 425–917–6590; email: 

sean.schauer@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 787–8 airplanes. The NPRM 

published in the Federal Register on 

July 24, 2015 (80 FR 43972) (‘‘the 

NPRM’’). The NPRM was prompted by 

reports indicating that the RAT 

assembly may fail to operate if deployed 

at low airspeeds. The NPRM proposed 

to require replacing either the RAT 

pump and control module assembly or 


jstallworth on DSK7TPTVN1PROD with RULES