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 


tkelley on DSK3SPTVN1PROD with PROPOSALS
81796 Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 

for corrosion or damage, and performing 

corrective actions. In addition, the 

service information describes 

procedures for installing a new forward 

trunnion pin housing assembly, seal, 

and retainer configuration. 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.’’ For 

information on the procedures and 

compliance times, see this service 

information at http://regulations.gov by 

searching for and locating Docket No. 

FAA–2015–8133. 

The phrase ‘‘related investigative 

actions’’ is used in this proposed AD. 

‘‘Related investigative actions’’ are 

follow-on actions that (1) are related to 

the primary actions, and (2) further 

investigate the nature of any condition 

found. Related investigative actions in 

an AD could include, for example, 

inspections. 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Costs of Compliance 

We estimate that this proposed AD 

affects 1,023 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 

Lubrication .............................. 2 work-hours × $85 per hour = $170, per lubrication cycle.$0 $170 $173,190, per lubrication 

cycle (1,023 airplanes). 

Inspection (Groups 1 and 2, 

Configuration 1 airplanes).

51 work-hours × $85 per hour = $4,335, per 

inspection cycle.

0 4,335 $4,282,980, per inspection 

cycle (988 airplanes). 

Inspection (Group 3 airplanes) 93 work-hours × $85 per hour = $7,905, per 

inspection cycle.

0 7,905 $276,675, per inspection 

cycle (35 airplanes). 

Replacement/overhaul 

(Groups 1 and 2).

84 work-hours × $85 per hour = $7,140 ........ 0 7,140 7,054,320 (988 airplanes). 

Replacement/overhaul (Group 

3 airplanes).

86 work-hours × $85 per hour = $7,310 ........ 0 7,310 $255,850 (35 airplanes). 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

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– 

2015–8133; Directorate Identifier 2015– 

NM–101–AD. 

(a) Comments Due Date 

We must receive comments by February 

16, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to certain The Boeing 

Company Model 737–600, –700, –700C, 

–800, –900, and -900ER series airplanes, 

certificated in any category, as identified in 

Boeing Special Attention Service Bulletin 

737–32–1448, Revision 1, dated May 29, 

2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 


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Federal Register / Vol. 80, No. 251 / Thursday, December 31, 2015 / Proposed Rules 81797 

(e) Unsafe Condition 

This AD was prompted by reports of heavy 

corrosion and chrome damage of the forward 

and aft trunnion pin assemblies of the right 

and left main landing gears (MLG). We are 

issuing this AD to detect and correct heavy 

corrosion and chrome damage of 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. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Repetitive Lubrication of MLG Trunnion 

Pin Assemblies 

For airplanes in Groups 1 and 2, 

Configuration 1, and airplanes in Group 3, as 

identified in Boeing Special Attention 

Service Bulletin 737–32–1448, Revision 1, 

dated May 29, 2015: Except as required by 

paragraph (k) of this AD, at the applicable 

time specified in Table 1 or Table 2 of 

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

Special Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015, 

lubricate the forward and aft trunnion pin 

assemblies of the left and right MLGs, in 

accordance with Work Package 1 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015. Repeat 

the lubrication thereafter at intervals not to 

exceed those specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 737–32–1448, Revision 1, 

dated May 29, 2015. Accomplishment of 

paragraph (i) of this AD terminates the 

repetitive lubrication required by this 

paragraph. 

(h) Repetitive Inspections, Corrective 

Actions, and Lubrication 

For airplanes in Groups 1 and 2, 

Configuration 1, and airplanes in Group 3, as 

identified in Boeing Special Attention 

Service Bulletin 737–32–1448, Revision 1, 

dated May 29, 2015: Except as required by 

paragraph (k) of this AD, at the applicable 

time specified in Table 1 or Table 2 of 

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

Special Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015, do a 

general visual inspection of the left and right 

MLGs at the forward and aft trunnion pin 

locations and the visible surfaces of the 

forward and aft trunnion pin assemblies for 

signs of corrosion or chrome plating damage 

and lubricate the forward and aft trunnion 

pin assemblies, in accordance with Work 

Package 2 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–32–1448, Revision 1, 

dated May 29, 2015. Repeat the general 

visual inspections thereafter at intervals not 

to exceed those specified in paragraph 1.E., 

‘‘Compliance,’’ of Boeing Special Attention 

Service Bulletin 737–32–1448, Revision 1, 

dated May 29, 2015. If any discrepancy is 

found during any inspection required by this 

paragraph, before further flight, do all 

applicable related investigative and 

corrective actions in accordance with Work 

Package 2 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737 32–1448, Revision 1, 

dated May 29, 2015. Accomplishment of the 

actions required by paragraph (i) of this AD 

terminates the repetitive inspections required 

by this paragraph. 

(i) Modification of MLG Trunnion Pin 

Assemblies 

For airplanes in Groups 1 and 2, 

Configuration 1, and airplanes in Group 3, as 

identified in Boeing Special Attention 

Service Bulletin 737–32–1448, Revision 1, 

dated May 29, 2015: Except as required by 

paragraph (k) of this AD, at the applicable 

time specified in Table 1 or Table 2 of 

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

Special Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015, modify 

and lubricate the left and right MLG trunnion 

pin assemblies, and do all applicable related 

investigative and corrective actions, in 

accordance with Work Package 3 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015. 

Accomplishment of the actions in Work 

Package 3 of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 737–32–1448, Revision 1, 

dated May 29, 2015, terminates the repetitive 

lubrication required by paragraph (g) of this 

AD and the repetitive inspections required by 

paragraph (h) of this AD. 

(j) Replacement of MLG Forward Trunnion 

Pin Housing Assembly Seal and Retainer 

For airplanes in Groups 1 and 2, 

Configuration 2, as identified in Boeing 

Special Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015: At the 

applicable time specified in Table 3, 

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

Special Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015, 

replace the seal, retainer, and support ring 

assembly with a new seal and retainer 

configuration, install the forward trunnion 

pin assembly into the housing assembly, and 

lubricate the forward and aft trunnion pin 

assemblies for the left and right MLGs, in 

accordance with Work Package 4 of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015. 

(k) Exception to Service Information 

Specification 

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

Boeing Special Attention Service Bulletin 

737–32–1448, Revision 1, dated May 29, 

2015, specifies a compliance time ‘‘from the 

original issue date on this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time ‘‘after the effective 

date of this AD.’’ 

(l) Credit for Previous Actions 

This paragraph provides credit for the 

requirements of paragraph (g) of this AD, if 

those actions were performed before the 

effective date of this AD using Boeing Special 

Attention Service Bulletin 737–32–1448, 

dated May 19, 2011, which is not 

incorporated by reference in this AD. 

(m) 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 (n) 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, 

modification, or alteration 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. To be approved, the 

repair method, modification deviation, or 

alteration deviation must meet the 

certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(n) Related Information 

(1) For more information about this AD, 

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. 

(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. 2015–32850 Filed 12–30–15; 8:45 am] 

BILLING CODE 4910–13–P 


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