81792 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 

52948, September 2, 2015, at the modified 

area only. 

(2) Accomplishing the actions specified in 

paragraphs (i)(2)(i) and (i)(2)(ii) of this AD 

terminates the inspections required by 

paragraph (g) of AD 2014–20–10, 

Amendment 39–17983 (79 FR 60331, October 

7, 2014), at the modified area only, provided 

the actions are accomplished concurrently, or 

the actions specified in paragraph (i)(2)(ii) of 

this AD are done after accomplishing the 

actions specified in paragraph (i)(2)(i) of this 

AD. 

(i) The actions specified in paragraphs 

(g)(1) through (g)(4) of this AD on the left and 

right struts are done in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 777–71– 

0055, Revision 1, dated April 15, 2015; and 

the revision specified in paragraph (g)(5) of 

this AD is done. 

(ii) A one-time general visual inspection 

for hydraulic fluid contamination (including 

contamination caused by hydraulic fluid in 

its liquid, vapor, and/or solid (coked) form) 

of the interior of the strut forward dry bay, 

and all applicable related investigative and 

corrective actions (including checking drain 

lines for blockage due to hydraulic fluid 

coking, and cleaning or replacing drain lines 

to allow drainage) are done in accordance 

with the Accomplishment Instructions of 

Boeing Special Attention Service Bulletin 

777–54–0028, Revision 1, dated December 

10, 2013, except where Boeing Special 

Attention Service Bulletin 777–54–0028, 

Revision 1, dated December 10, 2013, 

specifies to contact Boeing for repair, the 

repair must be done using a method 

approved in accordance with the procedures 

specified in paragraph (k) of this AD. 

(j) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (g) of this AD, if those 

actions were performed before the effective 

date of this AD using Boeing Special 

Attention Service Bulletin 777–71–0055, 

dated June 12, 2014, which is not 

incorporated by reference in this AD. 

(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-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) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (k)(3)(i) and (k)(3)(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 Kevin Nguyen, Aerospace Engineer, 

Propulsion Branch, ANM–140S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6501; fax: 425–917–6590; 

email: kevin.nguyen@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 

December 21, 2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–32852 Filed 12–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8132; Directorate 

Identifier 2015–NM–127–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 certain 

Airbus Model A318, A319, A320, and 

A321 series airplanes. This proposed 

AD was prompted by a report of cracks 

found during maintenance inspections 

on certain lugs of the 10VU rack side 

fittings in the cockpit. This proposed 

AD would require repetitive inspections 

for cracking of the lugs on the 10VU 

rack side fittings, and repair of any 

cracking. We are proposing this AD to 

prevent loss of flight-critical 

information displayed to the flightcrew 

during a critical phase of flight, such as 

an approach or takeoff, which could 

result in loss of airplane control at an 

altitude insufficient for recovery. 

DATES: We must receive comments on 

this proposed AD by February 16, 2016. 

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: 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 proposed 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.airworth-eas@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–2015– 

8132; 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 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: 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 81793 

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–2015–8132; Directorate Identifier 

2015–NM–127–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 

Union, has issued EASA Airworthiness 

Directive 2015–0170, dated August 18, 

2015 (referred to after this as the 

Mandatory Continuing Airworthiness 

Information, or ‘‘the MCAI’’), to correct 

an unsafe condition for certain Airbus 

Model A318, A319, A320, and A321 

series airplanes. The MCAI states: 

During an unscheduled maintenance 

operation on an A330 aeroplane, the 10VU 

rack was removed for access and cracks were 

discovered on 10VU rack side fittings on lugs 

1, 3, and 4. As a similar design is installed 

on A320 family aeroplanes, a sampling 

review was done to determine the possible 

fleet impact. The result showed that several 

aeroplanes had cracked or broken 10VU rack 

side fittings. 

This condition, if not detected and 

corrected, could lead to a high vibration level 

on the primary flight- and navigation 

displays during critical flight phases (takeoff 

and landing), possibly creating reading 

difficulties for the crew. 

Prompted by these findings, Airbus 

developed mod 35869 to reinforce the 

affected rack fitting lugs. For in-service 

aeroplanes, Airbus published Service 

Bulletin (SB) A320–92–1087 to provide 

inspection and repair instructions. 

For the reasons described above, this 

[EASA] AD requires repetitive detailed 

inspections (DET) of the affected 10VU rack 

fitting lugs and, depending on findings, 

accomplishment of a repair. 

You may examine the MCAI in the 

AD docket on the Internet at http:// 

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

8132. 

Related Service Information Under 1 

CFR Part 51 

Airbus has issued Service Bulletin 

A320–92–1087, Revision 02, dated 

November 25, 2014. The service 

information describes procedures for 

repetitive inspections for cracking of the 

lugs on the 10VU rack side fittings, and 

repair of any cracking. 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 AD. 

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 these same 

type designs. 

Explanation of ‘‘RC’’ Procedures and 

Tests 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 procedures and tests 

in the service information are required 

for compliance with an AD. 

Differentiating these procedures and 

tests 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 procedures and tests 

identified as RC (required for 

compliance) in any service information 

have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As specified in a Note under the 

Accomplishment Instructions of the 

specified service information, 

procedures and tests that are identified 

as RC in any service information must 

be done to comply with the proposed 

AD. However, procedures and tests that 

are not identified as RC are 

recommended. Those procedures and 

tests that are not identified as RC may 

be deviated from using accepted 

methods in accordance with the 

operator’s maintenance or inspection 

program without obtaining approval of 

an alternative method of compliance 

(AMOC), provided the procedures and 

tests identified as RC can be done and 

the airplane can be put back in an 

airworthy condition. Any substitutions 

or changes to procedures or tests 

identified as RC will require approval of 

an AMOC. 

Costs of Compliance 

We estimate that this proposed AD 

affects 959 airplanes of U.S. registry. 

We also estimate that it would take 

about 2 work-hours per product to 

comply with the basic requirements of 

this proposed AD, and 1 work-hour per 

product to report inspection findings. 

The average labor rate is $85 per workhour. Based on these figures, we 

estimate the cost of this proposed AD on 

U.S. operators to be $244,545, or $255 

per product. 

In addition, we estimate that any 

necessary repair would take about 84 

work-hours, for a cost of $7,140 per 

product. We have received no definitive 

data that would enable us to provide 

part cost estimates for the on-condition 

actions specified in this proposed AD. 

We have no way of determining the 

number of aircraft that might need these 

actions. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is 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. 

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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
81794 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 

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): 

Airbus: Docket No. FAA–2015–8132; 

Directorate Identifier 2015–NM–127–AD. 

(a) Comments Due Date 

We must receive comments by February 

16, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Airbus airplanes 

identified in paragraphs (c)(1) through (c)(4) 

of this AD, certificated in any category; 

except airplanes on which Airbus 

Modification 35869 has been embodied in 

production. 

(1) Airbus Model A318–111, –112, –121, 

and –122 airplanes. 

(2) Airbus Model A319–111, –112, –113, 

–114, –115, –131, –132, and –133 airplanes. 

(3) Airbus Model A320–211, –212, –214, 

–231, –232, and –233 airplanes. 

(4) Airbus Model A321–111, –112, –131, 

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

(d) Subject 

Air Transport Association (ATA) of 

America Code 25, Equipment/Furnishings. 

(e) Reason 

This AD was prompted by a report of 

cracks found during maintenance inspections 

on certain lugs of the 10VU rack side fittings 

in the cockpit. We are issuing this AD to 

prevent loss of flight-critical information 

displayed to the flightcrew during a critical 

phase of flight, such as an approach or 

takeoff, which could result in loss of airplane 

control at an altitude insufficient for 

recovery. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Inspections and Repair 

At the later of the times specified in 

paragraphs (g)(1) and (g)(2) of this AD: Do a 

detailed inspection for cracking of the lugs 

on the 10VU rack side fittings in the cockpit, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

92–1087, Revision 02, dated November 25, 

2014. If any crack is found, before further 

flight, repair in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–92–1087, Revision 02, 

dated November 25, 2014. Repeat the 

inspection thereafter at intervals not to 

exceed 20,000 flight cycles or 40,000 flight 

hours, whichever occurs first. Repair of the 

10VU rack lugs does not terminate the 

repetitive inspections required by this 

paragraph. 

(1) Before the accumulation of 30,000 total 

flight cycles or 60,000 total flight hours, 

whichever occurs first since the airplane’s 

first flight. 

(2) Within 24 months after the effective 

date of this AD. 

(h) Reporting Requirement 

Submit a report of any findings (positive 

and negative) of any inspection required by 

paragraph (g) of this AD to Airbus at the 

address specified in paragraph (j)(2) of this 

AD, at the applicable time specified in 

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

(1) If the inspection was done on or after 

the effective date of this AD: Submit the 

report within 90 days after the inspection. 

(2) If the inspection was done before the 

effective date of this AD: Submit the report 

within 90 days after the effective date of this 

AD. 

(i) 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) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Airbus’s EASA Design 

Organization Approval (DOA). If approved by 

the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

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. 

(4) Required for Compliance (RC): If any 

service information contains procedures or 

tests that are identified as RC, those 

procedures and tests must be done to comply 

with this AD; any procedures or tests that are 

not identified as RC are recommended. Those 

procedures and tests that are not identified 


tkelley on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 81795 

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 procedures and tests identified as RC can 

be done and the airplane can be put back in 

an airworthy condition. Any substitutions or 

changes to procedures or tests identified as 

RC require approval of an AMOC. 

(j) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency (EASA) 

Airworthiness Directive 2015–0170, dated 

August 18, 2015, for related information. 

This MCAI may be found in the AD docket 

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

by searching for and locating Docket No. 

FAA–2015–8132. 

(2) For 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. 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. 

Issued in Renton, Washington, on 

December 18, 2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–32885 Filed 12–30–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–8133; Directorate 

Identifier 2015–NM–101–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 certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This proposed AD was 

prompted by reports of heavy corrosion 

and chrome damage on the forward and 

aft trunnion pin assemblies of the right 

and left main landing gears (MLGs). 

This proposed AD would require 

repetitive lubrication of the forward and 

aft trunnion pin assemblies of the right 

and left MLGs; repetitive inspections of 

these assemblies for corrosion and 

chrome damage, and related 

investigative and corrective actions if 

necessary; and the installation of new or 

modified trunnion pin assembly 

components, which would terminate the 

repetitive lubrication and repetitive 

inspections. We are proposing this AD 

to detect and correct heavy corrosion 

and chrome damage on the forward and 

aft trunnion pin assemblies of the right 

and left MLGs, which could result in 

cracking of these assemblies and 

collapse of the MLGs. 

DATES: We must receive comments on 

this proposed AD by February 16, 2016. 

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– 

8133. 

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– 

8133; 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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6450; fax: 

425–917–6590; email: alan.pohl@

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– 

2015–8133; Directorate Identifier 2015– 

NM–101–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 received reports of heavy 

corrosion and chrome damage of the 

forward and aft trunnion pin assemblies 

of the right and left main MLGs on 

Boeing Model 737–600, –700, –700C, 

–800, –900, and –900ER series 

airplanes. Investigation revealed that the 

lubrication between the forward and aft 

trunnion pin assemblies and the outer 

cylinder assembly bushings and the 

lubrication of the aft trunnion bearing 

ball was not sufficient to prevent wear 

and corrosion. It was also determined 

that the clearances between the forward 

and aft trunnion pin cross bolt bushings 

and the cross bolts could affect the rate 

of wear and corrosion of the MLG 

trunnion pin assemblies. Corrosion and 

chrome damage of the forward and aft 

trunnion pin assemblies of the right and 

left main MLGs, if not corrected, could 

result in cracking of these assemblies 

and collapse of the MLGs. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Boeing Special 

Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015. 

The service information describes 

procedures for lubricating the forward 

and aft trunnion pin assemblies on the 

left and right MLGs, inspecting the 

forward and aft trunnion pin assemblies 


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