Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 40057 

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, 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 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 proposed 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. 

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): 

Agusta S.p.A. Helicopters: Docket No. FAA– 

2012–0886; Directorate Identifier 2008– 

SW–067–AD. 

(a) Applicability 

This AD applies to Agusta Model AB139 

and AW139 helicopters, with a wire strike 

protection system (WSPS) top cable cutter 

assembly, part number (P/N) 423–83001–1, 

installed, which is part of the WSPS, P/N 

4G9540F00211 or P/N 4G9540F00311, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as inflight contact between the top cable cutter 

assembly and main rotor (M/R) blades. This 

condition could result in damage to the 

M/R blades and subsequent loss of helicopter 

control. 

(c) Comments Due Date 

We must receive comments by September 

3, 2013. 

(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) Within 200 hours time-in-service, 

remove the WSPS upper installation, P/N 

4G9540A00111, including top cable cutter 

assembly, P/N 423–83001–1. 

(2) Before installing a WSPS upper 

installation, P/N 4G9540A00111, either: 

(i) Rework the top cable cutter assembly, 

P/N 423–83001–1, in accordance with the 

Compliance Instructions, paragraph 3.1 

through 3.5, and Figure 1 of Agusta Bolletino 

Technico No. 139–126, dated June 20, 2008. 

Re-identify the top cable cutter assembly in 

a visible and permanent way by adding ‘‘BT 

139–126 Rev./’’ or ‘‘FAA’’ at the end of the 

part number; or 

(ii) Replace the top cable cutter assembly, 

P/N 423–83001–1, with an airworthy top 

cable cutter assembly that has been reworked 

and re-identified in accordance with 

paragraph (e)(2)(i) of this AD. 

(3) Do not install a top cable cutter 

assembly, P/N 423–83001–1, on any 

helicopter unless it has been reworked and 

re-identified in accordance with paragraph 

(e)(2)(i) of this AD. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Sharon Miles, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

sharon.y.miles@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 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2008–0148, dated August 5, 2008. You 

may view the EASA AD at http:// 

www.regulations.gov by searching for and 

locating it in Docket No. FAA–2012–0886. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5320: Fuselage Miscellaneous 

Structure. 

Issued in Fort Worth, Texas, on June 18, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–15951 Filed 7–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0467; Directorate 

Identifier 2013–NM–023–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

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 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by reports of certain 

sliding windows that were difficult to 

operate after landing. This proposed AD 

would require a detailed inspection to 

identify part numbers of sliding 

windows and sliding window seals, and 

modification if necessary. This 

proposed AD also includes an optional 

replacement. We are proposing this AD 

to detect and correct incorrect seals, 

which could lead to the functional loss 

of the sliding window as an exit, 

possibly preventing the flightcrew from 

safely evacuating the airplane during an 

emergency. 

DATES: We must receive comments on 

this proposed AD by August 19, 2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus, Airworthiness Office—EIAS, 1 


tkelley on DSK3SPTVN1PROD with PROPOSALS
40058 Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 

Rond Point Maurice Bellonte, 31707 

Blagnac Cedex, France; telephone +33 5 

61 93 36 96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. For 

PPG Aerospace service information 

identified in this proposed AD, contact 

PPG Aerospace, 12780 San Fernando 

Road, Sylmar, CA 91342; telephone 

818–362–6711; fax 818–362–0603; 

Internet http://corporateportal.ppg.com/ 

na/aerospace. You may review copies of 

the 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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 proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0467; Directorate Identifier 

2013–NM–023–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 based on 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 European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0011, 

dated January 15, 2013 (referred to after 

this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Several occurrences have been reported on 

A320 family aeroplanes of PPG sliding 

windows that were difficult to operate after 

landing. 

The investigation results revealed that 

when a seal having Part Number (P/N) 22– 

17–7640–1 or P/N 22–17–7640–2 is installed 

on a sliding window, closure of the window 

can create a vacuum between the 2 tubes of 

the pressure seal, leading to the window 

remaining stuck to the frame on the fuselage 

side, due to suction effect. 

This condition, if not detected and 

corrected, could lead to the functional loss of 

the sliding window as an exit, possibly 

preventing the flight crew from safely 

evacuating the aeroplane during an 

emergency. 

For the reasons described above, this 

[EASA] AD requires a one-time detailed 

inspection (DI) of the sliding windows and 

its seal to identify the affected sliding 

window seals and, depending on findings, 

accomplishment of the applicable corrective 

actions [corrective action includes a 

modification or replacement]. 

The subject area on certain Airbus 

Model A318, A319, and A321 series 

airplanes is almost identical to that on 

the affected Model A320 series 

airplanes. Therefore, those Model A318, 

A319, and A321 series airplanes may be 

subject to the unsafe condition revealed 

on the Model A320 series airplanes. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–56–1015, dated September 14, 

2012; and Service Bulletin A320–56– 

1016, including Appendices 01 and 02, 

dated September 14, 2012. PPG 

Aerospace has issued Service Bulletin 

165312–56–001, dated February 29, 

2012. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between This AD and the 

MCAI or Service Information 

While paragraph (2) of EASA AD 

2013–0011, dated January 15, 2013, 

requires modification of the sliding 

window seal before further flight, this 

AD requires modification of the sliding 

window seal within the compliance 

time specified in paragraph (g) of this 

AD. This difference has been 

coordinated with EASA. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 851 products of U.S. 

registry. We also estimate that it would 

take about 3 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$217,005, or $255 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 1 work-hour and require parts 

costing $0, for a cost of $85 per product. 

We have no way of determining the 

number of products that may need these 

actions. 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 128 / Wednesday, July 3, 2013 / Proposed Rules 40059 

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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed 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. 

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 AD: 

Airbus: Docket No. FAA–2013–0467; 

Directorate Identifier 2013–NM–023–AD. 

(a) Comments Due Date 

We must receive comments by August 19, 

2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A318– 

111, –112, –121, and –122 airplanes; Model 

A319–111, –112, –113, –114, –115, –131, 

–132, and –133 airplanes; Model A320–111, 

–211, –212, –214, –231, –232, and –233 

airplanes; and Model A321–111, –112, –131, 

–211, –212, –213, –231, and –232 airplanes; 

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 56, Windows. 

(e) Reason 

This AD was prompted by reports of 

certain sliding windows that were difficult to 

operate after landing. We are issuing this AD 

to detect and correct incorrect seals, which 

could lead to the functional loss of the 

sliding window as an exit, possibly 

preventing the flightcrew from safely 

evacuating the airplane during an emergency. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspection 

Within 750 flight cycles or 750 flight 

hours, or within 4 months, after the effective 

date of this AD, whichever occurs first: Do 

a detailed inspection to identify part 

numbers (P/Ns) of each window and seal of 

the left-hand (LH) and right-hand (RH) 

sliding windows and sliding window seals, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

56–1016, including Appendices 01 and 02, 

dated September 14, 2012. A review of 

airplane maintenance records is acceptable in 

lieu of this inspection if the part number of 

the window and seal of the LH and RH 

sliding windows and sliding window seals 

can be conclusively determined from that 

review. 

(h) Modification 

If a sliding window part number identified 

in table 1 to paragraph (h) of this AD is found 

during the inspection required by paragraph 

(g) of this AD, and the part number does not 

have modification amendment M, and does 

have sliding window seals having P/N 22– 

17–7640–1 or P/N 22–17–7640–2 installed: 

Within the compliance time specified in 

paragraph (g) of this AD, modify the sliding 

window seal, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–56–1015, dated 

September 14, 2012. 

TABLE 1 TO PARAGRAPH (h) OF THIS

AD—AFFECTED PPG AEROSPACE

SLIDING WINDOW PART NUMBERS

Left-hand Right-hand 

NP165312–1 ...................... NP165312–2 

NP165312–3 ...................... NP165312–4 

NP165312–5 ...................... NP165312–6 

NP165312–7 ...................... NP165312–8 

NP165312–9 ...................... NP165312–10 

NP165312–11 .................... NP165312–12 

(i) Optional Replacement 

For sliding windows identified as affected 

in paragraph (h) of this AD, replacement of 

a sliding window seal having P/N 22–17– 

7640–1 L/H or P/N 22–17–7640–2 R/H with 

a seal having P/N 22–17–7640–3 L/H or P/ 

N 22–17–7640–4 R/H, respectively done, in 

accordance with a method approved by 

either the Manager, International Branch, 

ANM–116, Transport Airplane Directorate, 

FAA, or the European Aviation Safety 

Agency (EASA) (or its delegated agent), is an 

acceptable alternative method of compliance 

with the modification required by paragraph 

(h) of this AD. 

Note 1 to paragraph (i) of this AD: 

Guidance for replacement of a sliding 

window seal can be found in Page Block 401 

of Sub-section 56–12–11 of the Airbus A318/ 

A319/A320/A321 Aircraft Maintenance 

Manual. 

(j) Exceptions to Requirements of Paragraphs 

(g) and (h) of this AD 

(1) Airplanes on which Airbus 

modification 153512 (installation of sliding 

window with P/N NP165312–13 and P/N 

NP165312–14 with improved seal) or 

modification 153534 (installation of sliding 

window with P/N NP165312–11 and P/N 

NP165312–12 with amendment M) has been 

embodied in production are not affected by 

the requirements of paragraphs (g) and (h) of 

this AD, provided that no sliding window or 

sliding window seal has been replaced since 

first flight. 

(2) Airplanes on which Airbus 

modification 39587 (installation of affected 

seal on PPG Aerospace sliding windows) has 

not been embodied in production are not 

affected by the requirements of paragraphs (g) 

and (h) of this AD, provided that no sliding 

window or sliding window seal has been 

replaced since first flight. 

(k) Parts Installation Limitation 

As of the effective date of this AD, no 

person may install on any airplane any PPG 

Aerospace sliding window with a part 

number listed in table 1 to paragraph (h) of 

this AD with a seal having P/N 22–17–7640– 

1 or P/N 22–17–7640–2, unless the seal has 

been modified in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–56–1015, dated 

September 14, 2012; or PPG Aerospace 

Service Bulletin 165312–56–001, dated 

February 29, 2012. 

(l) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

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. The AMOC 

approval letter must specifically reference 

this AD. 

(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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
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actions are considered FAA-approved 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. 

(m) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2013–0011, dated 

January 15, 2013, for related information. 

(2) For Airbus service information 

identified in this AD, contact Airbus, 

Airworthiness Office—EIAS, 1 Rond Point 

Maurice Bellonte, 31707 Blagnac Cedex, 

France; telephone +33 5 61 93 36 96; fax +33 

5 61 93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. For PPG Aerospace service 

information identified in this AD, contact 

PPG Aerospace, 12780 San Fernando Road, 

Sylmar, CA 91342; telephone 818 362 6711; 

fax 818 362 0603; Internet http:// 

corporateportal.ppg.com/na/aerospace. You 

may review copies of the 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 June 14, 

2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–15947 Filed 7–2–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0468; Directorate 

Identifier 2012–NM–147–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 supersede an 

existing airworthiness directive (AD) 

that applies to certain The Boeing 

Company Model 777–200 and –300 

series airplanes equipped with RollsRoyce engines. The existing AD 

currently requires repetitive inspections 

to detect cracks of the outer V-blades of 

the thrust reverser, and corrective action 

if necessary. The existing AD also 

provides for optional terminating action 

for the repetitive inspections. Since we 

issued that AD, we have received 

reports of cracked outer V-blade fittings 

at the hinge beam end of Rolls-Royce 

engine thrust reversers, on airplanes on 

which the optional terminating action 

was done. This proposed AD would 

add, for airplanes on which the optional 

terminating action is done, repetitive 

inspections for cracking in the outer Vblade fittings of the hinge beam and 

latch beam ends of each thrust reverser 

half, and replacement of an affected 

thrust reverser half if necessary. This 

proposed AD would also add airplanes 

to the applicability. We are proposing 

this AD to prevent separation of a thrust 

reverser from the airplane during 

normal reverse thrust or during a 

refused takeoff, which could result in 

unexpected thrust asymmetry and a 

possible runway excursion. 

DATES: We must receive comments on 

this proposed AD by August 19, 2013. 

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 AD, 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 review copies of the 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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; 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: 

Melanie Violette, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6422; fax: 

425–917–6590; email: 

melanie.violette@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0468; Directorate Identifier 

2012–NM–147–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 

On December 14, 2006, we issued AD 

2006–26–06, Amendment 39–14864 (71 

FR 77586, December 27, 2006), for 

certain The Boeing Company Model 

777–200 and –300 series airplanes, 

equipped with Rolls-Royce engines, as 

identified in Boeing Special Attention 

Service Bulletin 777–78–0064, Revision 

1, dated November 30, 2006. That AD 

requires repetitive inspections to detect 

cracks of the outer V-blades of the thrust 

reverser, and corrective action if 

necessary. The existing AD also 

provides for optional terminating action 

for the repetitive inspections. That AD 

resulted from reports of cracked outer Vblades in the thrust reversers. We issued 

that AD to prevent separation of a thrust 

reverser from the airplane during 

normal reverse thrust or during a 

refused takeoff, which could result in 

impact damage to other airplane areas. 

If a thrust reverser separates from the 

airplane during a refused takeoff, the 

engine could produce forward thrust, 

resulting in unexpected thrust 

asymmetry and a possible runway 

excursion. 

Actions Since Existing AD 2006–26–06, 

Amendment 39–14864 (71 FR 77586, 

December 27, 2006) Was Issued 

Since we issued AD 2006–26–06, 

Amendment 39–14864 (71 FR 77586, 

December 27, 2006), we have received 

reports of cracked outer V-blade fittings 

at the hinge beam end of the thrust 


tkelley on DSK3SPTVN1PROD with PROPOSALS