Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 21713 

effective date of this AD), following DaherSocata Mandatory Service Bulletin SB 150– 

32, Revision 2, dated January 1994. 

(h) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Albert Mercado, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4119; fax: (816) 329– 

4090; email: albert.mercado@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer or other source, 

use these actions if they are FAA-approved. 

Corrective actions are considered FAAapproved if they are approved by the State 

of Design Authority (or their delegated 

agent). You are required to assure the product 

is airworthy before it is returned to service. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD 2015–0203, dated 

October 7, 2015; and Daher-Socata 

Mandatory Service Bulletin SB 150–32, 

Revision 2, dated January 1994, for related 

information. The MCAI can be found in the 

AD docket on the Internet at: http://

www.regulations.gov/#!documentDetail;

D=FAA-2016-0068-0002. 

(j) 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) Daher-Socata Mandatory Service 

Bulletin SB 150–32, Revision 3, dated 

September 2015. 

(ii) Reserved. 

(3) For SOCATA service information 

identified in this AD, contact SOCATA, 

Direction des services, 65921 Tarbes Cedex 9, 

France; phone: +33 (0) 5 62 41 73 00; fax: +33 

(0) 5 62 41 76 54; email: info@

socata.daher.com; Internet: http://

www.tbm.aero/. For the United States, 

contact SOCATA NORTH AMERICA, North 

Perry Airport, 601 NE 10 Street, Pompano 

Beach, Florida 33060; phone: (954) 366– 

3331; Internet: http://

www.socatanorthamerica.com/default.htm. 

(4) You may view this service information 

at the 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–2016–0068. 

(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 

4, 2016. 

Pat Mullen, 

Acting Manager, Small Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2016–08262 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–2015–5914; Directorate 

Identifier 2014–SW–056–AD; Amendment 

39–18472; AD 2016–07–27] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Helicopters (formerly Eurocopter 

France) 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Airbus 

Helicopters Model SA341G and SA342J 

helicopters. This AD requires repetitive 

inspections of a certain part-numbered 

main rotor hub torsion bar (torsion bar). 

This AD was prompted by several cases 

of corrosion in the metal strands of the 

torsion bar. The actions of this AD are 

intended to detect corrosion and 

prevent failure of the torsion bar, loss of 

a main rotor blade, and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective May 18, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of May 18, 2016. 

ADDRESSES: For 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 the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

10101 Hillwood Pkwy, Room 6N–321, 

Fort Worth, TX 76177. It is also on the 

Internet at http://www.regulations.gov 

by searching for and locating Docket No. 

FAA–2015–5914. 

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– 

5914; or in person at the Docket 

Operations Office between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. The AD docket 

contains this AD, the European Aviation 

Safety Agency (EASA) AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 10101 

Hillwood Pkwy, Fort Worth, Texas 

76177; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On November 19, 2015, at 80 FR 

72390, the Federal Register published 

our notice of proposed rulemaking 

(NPRM), which proposed to amend 14 

CFR part 39 by adding an AD that 

would apply to Model SA341G and 

SA342J helicopters with a torsion bar 

part number 704A33633274 installed. 

The NPRM proposed to require 

removing and performing repetitive 

inspections of each torsion bar for a 

crack in the polyurethane (PU) coating, 

the dimension of the angle between the 

bushings, corrosion on the inside 

diameter of each bushing, the thickness 

of each bushing, the size of the inside 

diameter of each bushing, and missing 

varnish on the two faces of each 

bushing. The NPRM also proposed to 

require replacing the torsion bar before 

further flight if there is a crack in the PU 

coating of a torsion bar that matches or 

exceeds the damage criteria, if the angle 

of the torsion bar is 7 degrees or more, 

if any corrosion on a bushing cannot be 

removed by rubbing it with an abrasive 

pad, if the thickness of a bushing is less 

than 37.520 mm (1.477 in), or if the 

diameter of a bushing is larger than 

21,040 mm (.828 in). If varnish is 

missing from more than 15 percent of 

the surface area from a face of a bushing, 

the NPRM proposed to require removing 

all varnish, finishing with an abrasive 

pad, and applying a coat of paint to the 

face of the bushing. The proposed 

requirements were intended to detect 

corrosion and prevent failure of the 


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21714 Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 

torsion bar, loss of a main rotor blade, 

and subsequent loss of control of the 

helicopter. 

The NPRM was prompted by AD No. 

2014–0216, dated September 24, 2014, 

issued by EASA, which is the Technical 

Agent for the Member States of the 

European Union, to correct an unsafe 

condition for Airbus Helicopters Model 

SA341G and SA342J helicopters. EASA 

advises that several cases of cracks were 

found on the PU coating of partnumbered 704A33633274 torsion bars 

installed on military Model SA341 

helicopters. EASA states that these parts 

can also be installed on civilian Model 

SA341 and SA342 helicopters. 

According to EASA, analysis of the 

cracked torsion bars showed small areas 

of superficial corrosion on the strands 

inside the bars can also develop during 

the manufacturing process. EASA states 

that cracking of the PU coating near 

these areas and the associated 

penetration of water can lead to further 

and deeper development of the 

corrosion. EASA advises that this 

condition, if not detected and corrected, 

allows water to penetrate into the 

torsion bar causing corrosion and failure 

of the metal strands inside the bar. 

Failure of the metal strands could lead 

to torsion bar failure, resulting in an inflight loss of a main rotor blade and 

consequent loss of control of the 

helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (80 FR 72390, November 19, 

2015). 

FAA’s Determination 

These helicopters have been approved 

by the aviation authority of France and 

are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed. 

Interim Action 

We consider this AD to be an interim 

action. If final action is later identified, 

we might consider further rulemaking. 

Differences Between This AD and the 

EASA AD 

This AD requires you to replace a 

torsion bar instead of returning it to the 

manufacturer for examination. 

Related Service Information Under 1 

CFR Part 51 

Eurocopter (now Airbus Helicopters) 

has issued 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, which describes 

inspecting the torsion bars for a crack in 

the PU coating and for corrosion and 

thickness of the bushings. 

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. 

Other Related Service Information 

Airbus Helicopters has also issued 

Alert Service Bulletin No. SA341/ 

SA342–05.40, Revision 0, dated April 

28, 2014 (ASB), for Model SA341G and 

SA342J helicopters certificated by the 

FAA, and military Model SA341B, C, D, 

E, F, and H and SA342K, L, L1, M, M1, 

and Ma helicopters. The ASB specifies 

repetitively inspecting the torsion bars 

in accordance with certain work cards, 

including work card 65.12.607. These 

inspections are part of Airbus 

Helicopters’ current maintenance 

program, and the ASB revises the 

compliance time interval for the 

inspections. 

Costs of Compliance 

We estimate that this AD affects 33 

helicopters of U.S. Registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD. 

We estimate $85 per work-hour for 

labor. We estimate 8 work-hours to 

inspect each helicopter at an estimated 

cost of $680 per helicopter and $22,440 

for the U.S. fleet per inspection cycle. 

Replacing a torsion bar will cost $7,020 

for required parts; no additional labor is 

necessary. 

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 

helicopters 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 to the extent that it justifies 

making a regulatory distinction; 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. 

We prepared an economic evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

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): 

2016–07–27 Airbus Helicopters (formerly 

Eurocopter France): Amendment 39– 

18472; Docket No. FAA–2015–5914; 

Directorate Identifier 2014–SW–056–AD. 


jstallworth on DSK7TPTVN1PROD with RULES
Federal Register / Vol. 81, No. 71 / Wednesday, April 13, 2016 / Rules and Regulations 21715 

(a) Applicability 

This AD applies to Model SA341G and 

SA342J helicopters with a main rotor head 

torsion bar (torsion bar) part number 

704A33633274 installed, certificated in any 

category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the coating of the torsion bar 

resulting in corrosion. This condition could 

result in failure of a torsion bar, loss of a 

main rotor blade, and subsequent loss of 

control of the helicopter. 

(c) Effective Date 

This AD becomes effective May 18, 2016. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) For each torsion bar with less than 5 

years since the first date of installation on 

any helicopter, within the compliance time 

shown in Table 1 to paragraph (e)(1) of this 

AD: 

(i) Remove the torsion bar and, using a 

magnifying glass with a maximum 

magnification level of 10X, visually inspect 

for a crack in the polyurethane (PU) coating 

of the torsion bar as depicted in Figure 1 of 

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. This type of task is 

commonly called a ‘‘work card’’ and will be 

referenced in this AD as ‘‘the work card.’’ 

Consider two cracks that are less than 5 mm 

(.196 in) apart as a single crack. If there is a 

crack in the PU coating that is more than 5 

mm (.196 in), replace the torsion bar before 

further flight. Do not rework the PU coating 

of the torsion bar in any way. 

(ii) Inspect the angle, dimension alpha, as 

depicted in View on Arrow F of Figure 1 of 

the work card. If the angle is 7 or more 

degrees, replace the torsion bar before further 

flight. 

(iii) Inspect each bushing for corrosion on 

the inside diameter. If any corrosion cannot 

be removed by rubbing it with an abrasive 

pad, replace the torsion bar before further 

flight. 

(iv) Using an outside micrometer, measure 

the thickness, dimension a, of each bushing 

as depicted in Detail AA of Figure 1 of the 

work card. If the thickness is less than 37.520 

mm (1.477 in), replace the torsion bar before 

further flight. 

(v) Using an inside micrometer, measure 

the inside diameter, dimension b, of each 

bushing as depicted in Detail AA of Figure 

1 of the work card. If the diameter is larger 

than 21.040 mm (.828 in), replace the torsion 

bar before further flight. 

(vi) Inspect the two faces of each bushing 

for missing varnish. If varnish is missing 

from more than 15% of the surface area on 

a face of a bushing, before further flight, 

remove all varnish using 400-grit abrasive 

paper. Finish with an abrasive pad and apply 

a coat of P05 paint to the face of the bushing. 

TABLE 1 TO PARAGRAPH (e)(1) 

Time accumulated on torsion bar Compliance time 

(i) Less than 320 hours time-in-service (TIS) since new and has never 

been inspected in accordance with Airbus Helicopters 341G—342J 

Airworthiness Limitations, Revision 18, dated June 2014 (limitations 

inspection).

Before accumulating 420 hours TIS since new or within 24 months 

since the date of first installation on any helicopter, whichever occurs 

first. 

(ii) 320 or more hours TIS since new and has never had a limitations 

inspection.

Within 100 hours TIS, or before accumulating 600 hours TIS since 

new, or within 24 months since the date of first installation on any 

helicopter, whichever occurs first. 

(iii) Less than 320 hours TIS since the last limitations inspection ........... Before accumulating 420 hours TIS since the last limitations inspection 

or within 24 months since the last limitations inspection, whichever 

occurs first. 

(iv) 320 or more hours TIS since the last limitations inspection .............. Within 100 hours TIS, or before accumulating 600 hours TIS since the 

last limitations inspection, or within 24 months since the last limitations inspection, whichever occurs first. 

(2) For each torsion bar with 5 or more 

years since the first date of installation on 

any helicopter, within the compliance time 

shown in Table 2 to paragraph (e)(2) of this 

AD, do the inspections required by 

paragraphs (e)(1)(i) through (vi) of this AD. 

TABLE 2 TO PARAGRAPH (e)(2) 

Time accumulated on torsion bar Compliance time 

(i) Less than 320 hours TIS since new, and less than 6 months since 

the date of first installation on any helicopter, and has never had a 

limitations inspection.

Before accumulating 420 hours TIS since new or within 12 months 

since the date of first installation on any helicopter, whichever occurs 

first. 

(ii) 320 or more hours TIS since new or more than 6 months since the 

date of first installation on any helicopter, and has never had a limitations inspection.

Within 100 hours TIS, or within 6 months, or before accumulating 600 

hours TIS since new, or within 24 months since the date of first installation on any helicopter, whichever occurs first. 

(iii) Less than 320 hours TIS since last limitations inspection and less 

than 6 months since the last limitations inspection.

Before accumulating 420 hours TIS since last limitations inspection or 

12 months since last limitations inspection, whichever occurs first. 

(iv) 320 or more hours TIS since last limitations inspection or 6 or more 

months since the last limitations inspection.

Within 100 hours TIS, or within 6 months, or before accumulating 600 

hours TIS since the last limitations inspection, or within 24 months 

since the last limitations inspection, whichever occurs first. 

(3) Repeat the inspections required by 

paragraphs (e)(1)(i) through (vi) of this AD as 

follows: 

(i) For torsion bars with less than 6 years 

since the date of installation on any 

helicopter, at intervals not to exceed 420 

hours TIS or 24 months, whichever occurs 

first. 

(ii) For torsion bars with 6 or more years 

since the date of installation on any 

helicopter, at intervals not to exceed 420 

hours TIS or 12 months, whichever comes 

first. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 10101 Hillwood Pkwy, Fort 


jstallworth on DSK7TPTVN1PROD with RULES
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