23900 Federal Register / Vol. 79, No. 82 / Tuesday, April 29, 2014 / Rules and Regulations 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2013–0208, dated 

September 10, 2013, for related information. 

The MCAI can be found in the AD docket on 

the Internet at: http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0020-0002. 

For availability information about APPH Ltd. 

Service Bulletin 32–40, at Initial Issue dated 

June 21, 1989, which is not incorporated by 

reference, use the contact information in 

paragraphs (j)(4) and (j)(5). 

(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) APPH Ltd. Service Bulletin No. 32–19, 

Revision 4, dated April 3, 2013. 

(ii) APPH Ltd. Service Bulletin No. 32–40, 

Revision 1, dated February 2003. 

(iii) British Aerospace Jetstream Series 

3100 & 3200 Service Bulletin 32–A– 

JA851226, Revision 5, dated April 30, 2013. 

(iv) Jetstream Service Bulletin 32– 

JA880340, original issue, dated January 6, 

1989. 

(3) For British Aerospace (Operations) 

Limited and Jetstream service information 

identified in this AD, contact BAE Systems 

(Operations) Ltd, Customer Information 

Department, Prestwick International Airport, 

Ayrshire, KA9 2RW, Scotland, United 

Kingdom; phone: +44 1292 675207, fax: +44 

1292 675704; email: RApublications@

baesystems.com; Internet: http://

www.jetstreamcentral.com. 

(4) For APPH Ltd. service information 

identified in this AD, contact APPH Ltd. 

Engineering Division, Unit 1, Pembroke 

Court, Chancellor Road, Manor Park, 

Runcorn, Cheshire, WA7 1TG, England; 

phone: +44 01928 532600; fax: +44 01928 

579626; Internet: http://apph.com/contactus/customer-support/. 

(5) You may view this service information 

at FAA, Small Airplane Directorate, 901 

Locust, Kansas City, Missouri 64106. For 

information on the availability of this 

material at the FAA, call (816) 329–4148. 

(6) 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, 2014. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2014–09540 Filed 4–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0233; Directorate 

Identifier 2014–NM–053–AD; Amendment 

39–17825; AD 2014–08–01] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2014–03– 

08 for all Airbus Model A318, A319, 

A320, and A321 series airplanes. AD 

2014–03–08 required an inspection to 

determine the part number of the 

interconnecting struts installed on the 

wings, identifying the part number and 

the serial number of the associated 

target and proximity sensor if 

applicable, and replacing or reidentifying the flap interconnecting 

strut if applicable. This new AD corrects 

a typographical error that affects the 

definition of a serviceable 

interconnecting strut. This AD was 

prompted by a report that an 

investigation showed that when a 

certain combination of a target/

proximity sensor serial number is 

installed on a flap interconnecting strut, 

a ‘‘target FAR’’ signal cannot be detected 

when it reaches the mechanical end 

stop of the interconnecting strut. We are 

issuing this AD to detect and correct a 

latent failure of the flap down drive 

disconnection due to an already-failed 

interconnecting strut sensor, which 

could result in asymmetric flap panel 

movement and consequent loss of 

control of the airplane. 

DATES: This AD becomes effective May 

14, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of March 26, 2014 (79 FR 9398, 

February 19, 2014). 

We must receive comments on this 

AD by June 13, 2014. 

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 service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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. 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. 

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–2014– 

0233; 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 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, WA 

98057–3356; telephone (425) 227–1405; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 22, 2014, we issued AD 

2014–03–08, Amendment 39–17745 (79 

FR 9398, February 19, 2014). AD 2014– 

03–08 applied to all Airbus Model 

A318, A319, A320, and A321 series 


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airplanes. AD 2014–03–08 was 

prompted by a report that an 

investigation showed that when a 

certain combination of a target/

proximity sensor serial number is 

installed on a flap interconnecting strut, 

a ‘‘target FAR’’ signal cannot be detected 

when it reaches the mechanical end 

stop of the interconnecting strut. AD 

2014–03–08 required an inspection to 

determine the part number of the 

interconnecting struts installed on the 

wings, identifying the part number and 

the serial number of the associated 

target and proximity sensor if 

applicable, and replacing or reidentifying the flap interconnecting 

strut if applicable. We issued AD 2014– 

03–08 to detect and correct a latent 

failure of the flap down drive 

disconnection due to an already-failed 

interconnecting strut sensor, which 

could result in asymmetric flap panel 

movement and consequent loss of 

control of the airplane. 

Since we issued AD 2014–03–08, 

Amendment 39–17745 (79 FR 9398, 

February 19, 2014), we identified a 

typographical error that affects the 

definition of a serviceable 

interconnecting strut. 

FAA’s Determination and Requirements 

of This 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 issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

FAA’s Determination of the Effective 

Date 

This new AD merely corrects a 

typographical error that affects the 

definition of a serviceable 

interconnecting strut. The requirements 

of this AD are substantially similar to 

the requirements of superseded AD 

2014–03–08, Amendment 39–17745, (79 

FR 9398, February 19, 2014). Therefore, 

we find that notice and opportunity for 

prior public comment are unnecessary 

and that good cause exists for making 

this amendment effective in less than 30 

days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES section. 

Include ‘‘Docket No. FAA–2014–0233; 

Directorate Identifier 2014–NM–053– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 

Costs of Compliance 

We estimate that this AD affects 755 

airplanes of U.S. registry. 

The actions that were required by AD 

2014–03–08, Amendment 39–17745 (79 

FR 9398, February 19, 2014), and are 

retained in this AD take about 8 workhours per product, at an average labor 

rate of $85 per work-hour. Required 

parts cost about $0 per product. Based 

on these figures, the estimated cost of 

the actions that were required by AD 

2014–03–08 is $680 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 10 work-hours and require parts 

costing $0, for a cost of $850 per 

product. We have no way of 

determining the number of aircraft that 

might need this action. 

The new requirements of this AD add 

no additional economic burden. 

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 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 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. 

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 

removing airworthiness directive (AD) 

2014–03–08, Amendment 39–17745 (79 

FR 9398, February 19, 2014), and adding 

the following new AD: 

2014–08–01 Airbus: Amendment 39–17825. 

Docket No. FAA–2014–0233; Directorate 

Identifier 2014–NM–053–AD. 

(a) Effective Date 

This AD becomes effective May 14, 2014. 

(b) Affected ADs 

This AD supersedes AD 2014–03–08, 

Amendment 39–17745 (79 FR 9398, February 

19, 2014). 

(c) Applicability 

This AD applies to all 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, 


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

certificated in any category; all manufacturer 

serial numbers. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight controls. 

(e) Reason 

This AD was prompted by a report that an 

investigation showed that when a certain 

combination of a target/proximity sensor 

serial number is installed on a flap 

interconnecting strut, a ‘‘target FAR’’ signal 

cannot be detected when reaching the 

mechanical end stop of the interconnecting 

strut. We are issuing this AD to detect and 

correct a latent failure of the flap down drive 

disconnection due to an already-failed 

interconnecting strut sensor, which could 

result in asymmetric flap panel movement 

and consequent loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Inspection To Determine the 

Part Number of the Interconnecting Struts 

This paragraph restates the requirements of 

AD 2014–03–08, Amendment 39–17745 (79 

FR 9398, February 19, 2014), with a corrected 

typographical error in paragraph (g)(2)(i) of 

this AD that affects the definition of a 

serviceable interconnecting strut. Within 

8,000 flight hours after March 26, 2014 (the 

effective date of AD 2014 03–08), inspect to 

determine the part number of the 

interconnecting struts installed on both the 

left-hand (LH) and right-hand (RH) wings of 

the airplane, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1206, Revision 01, 

dated October 10, 2011. A review of the 

airplane maintenance records is acceptable 

for determining the part number of the 

installed interconnecting struts, in lieu of the 

inspection, if the part number of the installed 

interconnecting struts, and the part number 

and the serial number of the associated target 

and proximity sensor, can be conclusively 

determined from that review. 

(1) Airplanes on which Airbus 

Modification 27956 has been embodied in 

production, and on which no interconnecting 

strut has been replaced with a strut having 

a part number specified in figure 1 to 

paragraph (g) of this AD since the airplane’s 

first flight: No further work is required by 

paragraph (g) of this AD. 

(2) If, during the inspection required by the 

introductory text of paragraph (g) of this AD, 

any interconnecting strut is installed with a 

part number specified in figure 1 to 

paragraph (g) of this AD: Within 8,000 flight 

hours after March 26, 2014 (the effective date 

of AD 2014 03–08, Amendment 39–17745 (79 

FR 9398, February 19, 2014)), determine the 

part number and the serial number of the 

associated target and proximity sensor. 

(i) For airplanes having conditions 

specified in paragraphs (g)(2)(i)(A), 

(g)(2)(i)(B), (g)(2)(i)(C), and (g)(2)(i)(D) of this 

AD: Before further flight, replace the 

interconnecting strut with a serviceable unit, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

27–1206, Revision 01, dated October 10, 

2011. For the purposes of this AD, a 

serviceable interconnecting strut is a unit 

which has been determined to be in 

compliance with the requirements of this AD. 

(A) A target part number (P/N) ABS0121– 

13 or P/N 8–536–01; and 

(B) A target serial number lower than 1600, 

or a target serial number that is unreadable; 

and 

(C) A proximity sensor having P/N 

ABS0121–31 or P/N 8–372–04; and 

(D) A proximity sensor having a serial 

number between C59198 and C59435, or a 

serial number (S/N) C500000 or higher. 

(ii) For a target having S/N 1600 or higher 

and target P/N ABS0121–13 or P/N 8–536– 

01: Within 8,000 flight hours after March 26, 

2014 (the effective date of AD 2014 03–08, 

Amendment 39–17745 (79 FR 9398, February 

19, 2014), re-identify the interconnecting 

strut, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–27–1206, Revision 01, 

dated October 10, 2011. 

FIGURE 1 TO PARAGRAPH (g) OF THIS

AD—INTERCONNECTING STRUT

PART NOS. 

Interconnecting strut part Nos. 

D5757030500000 

D5757030500100 

D5757030500200 

D5757030500600 

D5757030500800 

D5757030501000 

D5757030501200 

D5757032200000 

(h) Retained Parts Installation Prohibition 

This paragraph restates the requirements of 

AD 2014–03–08, Amendment 39–17745 (79 

FR 9398, February 19, 2014). As of March 26, 

2014 (the effective date of AD 2014 03–08), 

no person may install an interconnecting 

strut with a part number specified in figure 

1 to paragraph (g) of this AD, on any airplane, 

except for parts identified in paragraph 

(g)(2)(ii) of this AD, provided that the actions 

in paragraph (g)(2)(ii) are done. 

(i) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (g) of this AD, 

if those actions were performed before March 

26, 2014 (the effective date of AD 2014 03– 

08, Amendment 39–17745 (79 FR 9398, 

February 19, 2014)), using Airbus Service 

Bulletin A320–27–1206, dated January 28, 

2011, and if additional work has been 

accomplished using Airbus Service Bulletin 

A320–27–1206, Revision 01, dated October 

10, 2011. Airbus Service Bulletin A320–27– 

1206, dated January 28, 2011, is not 

incorporated by reference in this AD. 

(j) 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, WA 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 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or its delegated agent, or the DAH with a 

State of Design Authority’s design 

organization approval, as applicable). You 

are required to assure the product is 

airworthy before it is returned to service. 

(k) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2012–0012, dated January 23, 2012, 

for related information. You may examine the 

MCAI on the Internet at http://

www.regulations.gov by searching for and 

locating Docket No. FAA–2014–0233. 

(2) Service information identified in this 

AD that is not incorporated by reference may 

be obtained at the addresses specified in 

paragraphs (l)(4) and (l)(5) of this AD. 

(l) 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 this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on March 26, 2014 (79 FR 

9398, February 19, 2014). 

(i) Airbus Service Bulletin A320–27–1206, 

Revision 01, dated October 10, 2011. 

(ii) Reserved. 

(4) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAS, 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.airworth-eas@airbus.com; Internet 

http://www.airbus.com. 

(5) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 


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(6) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on April 7, 

2014. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–09623 Filed 4–28–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0690; Directorate 

Identifier 2013–NM–088–AD; Amendment 

39–17835; AD 2014–08–11] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2009–24– 

07 for certain the Boeing Company 

Model 737–600, –700, –700C, and –800 

series airplanes. AD 2009–24–07 

required repetitive lubrications of the 

right and left main landing gear (MLG) 

forward trunnion pins. AD 2009–24–07 

also required an inspection for 

discrepancies of the transition radius of 

the MLG forward trunnion pins, and 

corrective actions if necessary. For 

certain airplanes, AD 2009–24–07 

required repetitive detailed inspections 

for discrepancies (including finish 

damage, corrosion, pitting, and base 

metal scratches) of the transition radius 

of the left and right MLG trunnion pins, 

and corrective action if necessary. 

Replacing or overhauling the trunnion 

pins terminates the actions required by 

AD 2009–24–07. This new AD adds 

airplanes to the applicability of AD 

2009–24–07. This AD was prompted by 

reports of corrosion protection damage 

to the forward trunnion pin on 

additional airplanes. We are issuing this 

AD to prevent stress corrosion cracking 

of the forward trunnion pins, which 

could result in fracture of the pins and 

consequent collapse of the MLG. 

DATES: This AD is effective June 3, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of June 3, 2014. 

ADDRESSES: 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. 

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–2013– 

0690; 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6440; fax: 

425–917–6590; email: nancy.marsh@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–24–07, 

Amendment 39–16095 (74 FR 62231, 

November 27, 2009). AD 2009–24–07 

applied to certain The Boeing Company 

Model 737–600, –700, –700C, and –800 

series airplanes. The NPRM published 

in the Federal Register on August 13, 

2013 (78 FR 49229). The NPRM was 

prompted by reports of corrosion 

protection damage to the forward 

trunnion pin on additional airplanes. 

The NPRM proposed to continue to 

require repetitive lubrications of the 

right and left main landing gear (MLG) 

forward trunnion pins. The NPRM also 

proposed to continue to require an 

inspection for discrepancies of the 

transition radius of the MLG forward 

trunnion pins, and corrective actions if 

necessary. For certain airplanes, the 

NPRM proposed to continue to require 

repetitive detailed inspections for 

discrepancies (including finish damage, 

corrosion, pitting, and base metal 

scratches) of the transition radius of the 

left and right MLG trunnion pins, and 

corrective action if necessary. Replacing 

or overhauling the trunnion pins would 

terminate the actions required by AD 

2009–24–07. The NPRM proposed to 

add airplanes to the applicability of AD 

2009–24–07. We are issuing this AD to 

prevent stress corrosion cracking of the 

forward trunnion pins, which could 

result in fracture of the pins and 

consequent collapse of the MLG. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 49229, 

August 13, 2013) and the FAA’s 

response to each comment. 

Concurrence With the NPRM (78 FR 

49229, August 13, 2013) 

Boeing stated that it concurs with the 

content of the NPRM (78 FR 49229, 

August 13, 2013). 

Supplemental Type Certificate (STC) 

Winglet Comment 

Aviation Partners Boeing stated that 

the installation of winglets per STC 

ST00830SE (http://rgl.faa.gov/

Regulatory_and_Guidance_Library/

rgstc.nsf/0/408E012E008616A786257

8880060456C?Open

Document&Highlight=st00830se) does 

not affect the accomplishment of the 

manufacturer’s service instructions. 

We have redesignated paragraph (c) of 

the NPRM (78 FR 49229, August 13, 

2013) as paragraph (c)(1) of this AD, and 

added paragraph (c)(2) to this AD to 

state that installation of STC ST00830SE 

(http://rgl.faa.gov/Regulatory_and_

Guidance_Library/rgstc.nsf/0/

408E012E008616A7862578880060456C?

OpenDocument&Highlight=st00830se) 

does not affect the ability to accomplish 

the actions required by this AD. 

Therefore, for airplanes on which STC 

ST00830SE is installed, a ‘‘change in 

product’’ alternative method of 

compliance (AMOC) approval request is 

not necessary to comply with the 

requirements of 14 CFR 39.17. For all 

other AMOC requests, the operator must 

request approval of an AMOC in 

accordance with the procedures 

specified in paragraph (l) of this AD. 

Request for Clarification of Location of 

Trunnion Pins 

Delta asked for clarification of the 

term ‘‘trunnion pins’’ as specified in the 


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