Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Proposed Rules 51491 

between fuselage station 655 and station 

1434 that has a scribe line 0.001 inch or 

deeper. 

(ii) Either an ultrasonic inspection or a 

surface HFEC inspection for cracks 

(depending on the location of the scribe 

line(s)) of any skin panel common to a 

stringer lap splice between fuselage station 

655 and station 1434 that has a scribe line 

0.001 inch or deeper. 

(iii) An external phased array ultrasonic 

inspection for cracks in the lower/overlapped 

skin of the stringer S–14L/R lap splices 

between fuselage station 655 and station 

1434. 

(iv) An open hole HFEC inspection for skin 

cracks at the upper and lower fastener rows 

of the stringer lap splices. 

(3) Inspection ‘‘C’’ includes the inspections 

for scribe lines and cracks specified in 

paragraphs (g)(3)(i), (g)(3)(ii), and (g)(3)(iii) of 

this AD on stringer S–14L/R lap splice 

between fuselage station 655 and station 

1434 on both sides of the airplane. 

(i) A detailed inspection for scribe lines. If 

any scribe line is found during the inspection 

required by this paragraph, the actions 

include the inspections specified in 

paragraphs (g)(3)(i)(A) and (g)(3)(i)(B) of this 

AD. 

(A) A detailed inspection for cracks of the 

scribe line area(s). 

(B) Either an ultrasonic inspection or a 

surface HFEC inspection for cracks 

(depending on the location of the scribe 

line(s)). 

(ii) An external phased array ultrasonic 

inspection for cracks in the lower/overlapped 

skin of the stringer lap splices between 

fuselage station 655 and station 1434. 

(iii) An open hole HFEC inspection for skin 

cracks at the upper and lower fastener rows 

of the stringer S–14L/R lap splices. 

(h) Exceptions to Service Information 

Specifications 

(1) Where Paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 777–53A0052, 

dated October 10, 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.’’ 

(2) If, during accomplishment of any 

inspection required by this AD, any 

condition is found for which Boeing Alert 

Service Bulletin 777–53A0052, dated October 

10, 2014, specifies to contact Boeing for 

special repair instructions or supplemental 

instructions for the modification, and 

specifies that action as ‘‘RC’’ (Required for 

Compliance): Before further flight, do the 

repair or modification using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(i) Lap Splice Modification 

At the applicable time specified in 

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

Alert Service Bulletin 777–53A0052, dated 

October 10, 2014: Do the left-side and rightside lap splice modification, in accordance 

with the Accomplishment Instructions of 

Boeing Alert Service Bulletin 777–53A0052, 

dated October 10, 2014, except as provided 

by paragraph (h)(2) of this AD. 

(j) Post-Modification Inspections and 

Corrective Action 

At the applicable time specified in 

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

Alert Service Bulletin 777–53A0052, dated 

October 10, 2014: Do a post-modification 

internal surface HFEC inspection for skin 

cracks in the modified lap splices on both 

sides of the airplane; and do all applicable 

corrective actions; in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 777–53A0052, dated October 

10, 2014, except as provided by paragraph 

(h)(2) of this AD. Do all applicable corrective 

actions before further flight. Repeat the 

inspection of the modified lap splices 

thereafter at the applicable intervals specified 

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

Alert Service Bulletin 777–53A0052, dated 

October 10, 2014. 

(k) 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 (l)(1) of this AD. Information may 

be emailed to: 9–ANM–Seattle–ACO–AMOC– 

Requests@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 

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. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (h)(2) 

of this AD: For service information that 

contains steps that are labeled as Required 

for Compliance (RC), the provisions of 

paragraphs (k)(4)(i) and (k)(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. 

(l) Related Information 

(1) For more information about this AD, 

contact Haytham Alaidy, Aerospace 

Engineer, Airframe Branch, ANM–120S, 

FAA, Seattle ACO, 1601 Lind Avenue SW., 

Renton, WA 98057–3356; phone: 425–917– 

6573; fax: 425–917–6590; email: 

Haytham.Aaidy@faa.gov. 

(2) 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. 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. 

Issued in Renton, Washington, on August 

17, 2015. 

Kevin Hull, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20853 Filed 8–24–15; 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] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all The 

Boeing Company Model 777–200, 

–200LR, –300, and –300ER series 

airplanes. This proposed 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 

proposed AD would 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. This 

proposed AD would also provide for 

optional terminating action for the 

repetitive inspections. We are proposing 

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. 


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DATES: We must receive comments on 

this proposed AD by October 9, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed 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. 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 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: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–3147; Directorate Identifier 2014– 

NM–094–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received reports of fractured 

forward attach fittings of the inboard 

flap outboard aft flap track, and it is 

believed to be the result of corrosion 

pits forming on the inside diameter of 

the fittings. Four operators have 

reported finding four fractured forward 

attach fittings of the aft flap track of the 

inboard flap on airplanes with 

approximately 20,300 to 31,900 total 

flight hours and approximately 5,900 to 

8,500 total flight cycles. In addition, two 

operators reported three cracked fittings 

on airplanes with approximately 29,300 

to 35,700 total flight hours and 

approximately 5,200 to 7,900 total flight 

cycles. This condition, if not corrected, 

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. 

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 eliminate the 

need for the 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 of this NPRM. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

This proposed AD would require 

accomplishing the actions specified in 

the service information described 

previously, except as discussed under 

‘‘Differences Between this Proposed AD 

and the Service Information.’’ Refer to 

this service information for details on 

the procedures and compliance times. 

Explanation of ‘‘RC’’ Steps in Service 

Information 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee (ARC), to 

enhance the AD system. One 

enhancement was a new process for 

annotating which steps in the service 

information are required for compliance 

with an AD. Differentiating these steps 

from other tasks in the service 

information is expected to improve an 

owner’s/operator’s understanding of 

crucial AD requirements and help 

provide consistent judgment in AD 

compliance. The steps identified as 

Required for Compliance (RC) in any 

service information identified 

previously have a direct effect on 

detecting, preventing, resolving, or 

eliminating an identified unsafe 

condition. 

For service information that contains 

steps that are labeled as RC, the 

following provisions apply: (1) 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, and an AMOC is required 

for any deviations to RC steps, including 

substeps and identified figures; and (2) 

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. 

Differences Between This Proposed AD 

and the Service Information 

Boeing Special Attention Service 

Bulletin 777–57–0094, Revision 1, dated 

November 5, 2014, specifies groups 1, 2, 

3, 4, and 5 airplanes as the effectivity. 

However, this proposed AD is 

applicable only to groups 1, 2, and 4 

airplanes (Model 777–200, –200LR, 

–300, and –300ER airplanes) because 

the identified unsafe condition only 

affects these airplanes. For groups 3 and 

5 airplanes (Model 777F airplanes), the 


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consequence of fitting fracture on these 

airplanes has not been determined to be 

an unsafe condition at this time. 

Therefore, we are not requiring 

inspections for groups 3 and 5 airplanes. 

We have coordinated this difference 

with Boeing. 

Costs of Compliance 

We estimate that this proposed AD 

affects 148 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed 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 would 

be required based on the results of the 

proposed 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 proposed 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 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would 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 this proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the 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. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 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): 

The Boeing Company: Docket No. FAA– 

2015–3147; Directorate Identifier 2014– 

NM–094–AD. 

(a) Comments Due Date 

We must receive comments by October 9, 

2015. 

(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. 

(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. 


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(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 inboard flap of 

the main flap 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 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 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. 

(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. 

(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, 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, 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, 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. 

(1) Replace 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. 

(2) Replace 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. 

(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. 

(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. 

(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. 

(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– 

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 

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. For a repair 

method to be approved, the repair 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 


asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 164 / Tuesday, August 25, 2015 / Proposed Rules 51495 

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 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

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

6590; email: Eric.Lin@faa.gov. 

(2) 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. 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. 

Issued in Renton, Washington, on August 

17, 2015. 

Kevin Hull, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–20835 Filed 8–24–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–3607; Directorate 

Identifier 2015–CE–010–AD] 

RIN 2120–AA64 

Airworthiness Directives; M7 

Aerospace LLC Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all M7 

Aerospace LLC Models SA26–AT, 

SA226–T, SA226–AT, SA226–T(B), 

SA226–TC, SA227–AT, SA227–TT, 

SA227–AC (C–26A), SA227–BC (C– 

26A), SA227–CC, and SA227–DC (C– 

26B) airplanes. This proposed AD was 

prompted by information that the 

airplane flight manual (AFM) does not 

provide adequate guidance in the 

handling of engine failures, which may 

lead to reliance on the negative torque 

system (NTS) for reducing drag. This 

condition could lead the pilot to not 

fully feather the propeller with 

consequent loss of control. This 

proposed AD would require inserting 

updates into the airplane flight manual 

(AFM) and/or the pilot operating 

handbook (POH) that will clearly 

establish that the NTS is not designed 

to automatically feather the propeller 

but only to provide drag protection. We 

are proposing this AD to correct the 

unsafe condition on these products. 

DATES: We must receive comments on 

this proposed AD by October 9, 2015. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact M7 

Aerospace LLC, 10823 NE Entrance 

Road, San Antonio, Texas 78216; phone: 

(210) 824–9421; fax: (210) 804–7766; 

Internet: http://www.elbitsystemsus.com; email: MetroTech@

M7Aerospace.com. You may view this 

referenced 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. 

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– 

3607; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Michael Heusser, Aerospace Engineer, 

FAA, Fort Worth Aircraft Certification 

Office, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone: (817) 

222–5038; fax: (817) 222–5960; email: 

Michael.A.Heusser@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2015–3607; Directorate Identifier 2015– 

CE–010–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The FAA received a report of an 

accident where an M7 Aerospace LLC 

Model SA227–AC airplane experienced 

left engine power loss and consequent 

loss of control. Training manuals 

provide descriptions of the negative 

torque system (NTS), which provides 

partial anti-drag protection if a negative 

torque condition is sensed. This feature 

might cause pilots to assume the system 

automatically provides full anti-drag 

protection in the event of an engine 

failure or power loss. The pilot must 

also take prompt action to fully feather 

the propeller on the failed engine to 

reduce drag. A pilot’s sole reliance on 

the NTS for reducing drag in the event 

of engine power loss may result in the 

pilot’s failure to initiate the Engine 

Failure Inflight checklist and feather the 

propellers in time. 

This condition, if not corrected, could 

result in loss of control of the aircraft 

due to excessive asymmetric drag. 

Related Service Information Under 1 

CFR Part 51 

We reviewed the following M7 

Aerospace LLC AFM revisions: 

• AFM revision dated May 14, 2015, 

section III, SA26–AT Dash One; 

• AFM revision dated May 14, 2015, 

section III, SA26–AT Dash Two; 

• AFM revision B–33, sections i and 

III, SA226–AT, dated November 14, 

2014; 

• AFM revision A–29, sections i and 

III, SA226–T, dated November 14, 2014; 

• AFM revision B–29, sections i and 

3, SA226–T(B), dated November 14, 

2014; 

• AFM revision A–43, sections i and 

III, SA226–TC, dated November 14, 

2014; 


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