59830 Federal Register / Vol. 81, No. 169 / Wednesday, August 31, 2016 / Rules and Regulations 

(4) TR 5–2–13, dated June 4, 2014, to Part 

2, Section 5–10–11, of Bombardier Global 

5000 BD–700 Time Limits/Maintenance 

Checks (for Model BD–700–1A11 airplanes). 

(5) TR 5–2–44, dated June 4, 2014, to Part 

2, Section 5–10–11, of Bombardier Global 

Express BD–700 Time Limits/Maintenance 

Checks (for Model BD–700–1A10 airplanes). 

(h) No Alternative Actions and Intervals 

After accomplishing the revision required 

by paragraph (g) of this AD, no alternative 

actions (e.g., inspections) and intervals may 

be used unless the actions and intervals are 

approved as an alternative method of 

compliance (AMOC) in accordance with the 

procedures specified in paragraph (k)(1) of 

this AD. 

(i) Replacement 

For airplanes identified in section 1.A., 

‘‘Effectivity,’’ of Bombardier Global 5000 

Service Bulletin 700–1A11–52–023, dated 

October 4, 2013; or Bombardier Global 

Express/Global Express XRS Service Bulletin 

700–52–046, dated October 4, 2013; except as 

provided by paragraph (j)(1) or (j)(2) of this 

AD: Within 15 months after the effective date 

of this AD, but not exceeding the applicable 

life limit of the passenger tensator spring 

identified in the applicable TR specified in 

paragraphs (g)(1) through (g)(5) of this AD, 

replace the passenger door tensator springs 

having part number (P/N) GS321–0580–1, 

with new springs, in accordance with the 

Accomplishment Instructions of Bombardier 

Global 5000 Service Bulletin 700–1A11–52– 

023, dated October 4, 2013; or Bombardier 

Global Express/Global Express XRS Service 

Bulletin 700–52–046, dated October 4, 2013; 

as applicable. 

(j) Acceptable Alternative Actions for 

Paragraph (i) of This AD 

(1) For airplanes having serial numbers (S/ 

N) 9278 through 9360 inclusive: Replacement 

of the passenger door tensator springs having 

P/N GS321–0580–1 with new springs before 

the effective date of this AD is acceptable for 

compliance with the requirements of 

paragraph (i) of this AD. Refer to the task 

specified in the applicable TRs identified in 

paragraphs (g)(1) through (g)(5) of this AD for 

subsequent spring replacements. 

(2) For airplanes with serial numbers other 

than those identified in paragraph (j)(1) of 

this AD: Accomplishment after the effective 

date of this AD of the ‘‘Time Limits/ 

Maintenance Checks’’ discard task identified 

in the applicable service information 

specified in paragraphs (g)(1) through (g)(5) 

of this AD is acceptable for compliance with 

the requirements of paragraph (i) of this AD. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, 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 New York ACO, send it to 

ATTN: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

NY 11590; telephone: 516–228–7300; fax: 

516–794–5531. 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, New York ACO, ANE–170, 

FAA; or Transport Canada Civil Aviation 

(TCCA); or Bombardier, Inc.’s TCCA Design 

Approval Organization (DAO). If approved by 

the DAO, the approval must include the 

DAO-authorized signature. 

(l) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

AD CF–2014–39, dated November 4, 2014, 

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–2016–3989. 

(m) 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. 

(i) Temporary Revision 5–2–7, dated June 

4, 2014, to Part 2, Section 5–10–11, of 

Bombardier Global Express XRS BD–700 

Time Limits/Maintenance Checks. 

(ii) Temporary Revision 5–2–10, dated 

September 9, 2014, to Part 2, Section 5–10– 

11, of Bombardier Global 5000 GL 5000 

Featuring Global Vision Flight Deck—Time 

Limits/Maintenance Checks. 

(iii) Temporary Revision 5–2–10, dated 

September 9, 2014, to Part 2, Section 5–10– 

11, of Bombardier Global 6000 GL 6000 Time 

Limits/Maintenance Checks. 

(iv) Temporary Revision 5–2–13, dated 

June 4, 2014, to Part 2, Section 5–10–11, of 

Bombardier Global 5000 BD–700 Time 

Limits/Maintenance Checks. 

(v) Temporary Revision 5–2–44, dated June 

4, 2014, to Part 2, Section 5–10–11, of 

Bombardier Global Express BD–700 Time 

Limits/Maintenance Checks. 

(vi) Bombardier Global Express/Global 

Express XRS Service Bulletin 700–52–046, 

dated October 4, 2013. 

(vii) Bombardier Global 5000 Service 

Bulletin 700–1A11–52–023, dated October 4, 

2013. 

(3) For service information identified in 

this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; email thd.crj@

aero.bombardier.com; Internet http://

www.bombardier.com. 

(4) 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. 

(5) 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 August 

18, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–20693 Filed 8–30–16; 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; Amendment 

39–18631; AD 2016–18–01] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–600, 

–700, –700C, –800, –900, and –900ER 

series airplanes. This 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 AD 

requires 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 installation of 

new or modified trunnion pin assembly 

components, which will terminate the 

repetitive lubrication and repetitive 

inspections. We are issuing 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: This AD is effective October 5, 

2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of October 5, 2016. 


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Federal Register / Vol. 81, No. 169 / Wednesday, August 31, 2016 / Rules and Regulations 59831 

ADDRESSES: For service information 

identified in this final rule, 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 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: 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to certain The Boeing Company 

Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes. The 

NPRM published in the Federal 

Register on December 31, 2015 (80 FR 

81795) (‘‘the NPRM’’). The NPRM was 

prompted by reports of heavy corrosion 

and chrome damage on the forward and 

aft trunnion pin assemblies of the right 

and left MLGs. The NPRM proposed to 

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 installation of 

new or modified trunnion pin assembly 

components, which would terminate the 

repetitive lubrication and repetitive 

inspections. We are issuing 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. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM and the FAA’s 

response to each comment. 

Support for the NPRM 

Boeing stated that it concurs with the 

contents of the NPRM. 

Effect of Winglets on Accomplishment 

of the Proposed Actions 

Aviation Partners Boeing stated that 

accomplishing Supplemental Type 

Certificate (STC) ST00830SE does not 

affect the accomplishment of the actions 

specified in the NPRM. 

We concur with the commenter. We 

have redesignated paragraph (c) of the 

proposed AD as paragraph (c)(1) and 

added new paragraph (c)(2) in this AD 

to state that installation of STC 

ST00830SE does not affect the ability to 

accomplish the actions required by this 

final rule. 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. 

Request for Clarification of 

Requirements 

Delta Airlines (DAL) requested an 

explanation of how the requirements are 

different between AD 2014–08–11, 

Amendment 39–17835 (79 FR 23903, 

April 29, 2014) (‘‘AD 2014–08–11’’) and 

the NPRM. DAL noted that the 

requirements of AD 2014–08–11 include 

an inspection for discrepancies of the 

transition radius of the MLG forward 

trunnion pins, and corrective actions if 

necessary. DAL elaborated that this 

inspection is for finish damage (scrapes 

through primer), signs of corrosion, 

pitting, and scratches in the base metal 

of that area. DAL pointed out that the 

NPRM requires a general visual 

inspection of the MLG forward trunnion 

pin assembly for signs of corrosion or 

chrome plating damage, and if either 

condition is found, a detailed inspection 

of the forward trunnion pin assembly is 

required. DAL mentioned that the 

detailed inspection requires verification 

that a new seal and retainer 

configuration is installed, and if the 

overhaul limits exceed what is specified 

in the component maintenance manual, 

replacement of the forward trunnion pin 

assembly is necessary. DAL reasoned 

that the forward trunnion pin 

inspections required by AD 2014–08–11 

should be superseded by the proposed 

forward trunnion pin inspections in the 

NPRM. DAL stated that the detailed 

inspection proposed in the NPRM has 

additional corrective actions if any loose 

or missing chrome plating is found, 

beyond what is required in AD 2014– 

08–11. DAL also conveyed that the 

inspections for signs of corrosion are the 

same in the NPRM and AD 2014–08–11. 

We agree to provide clarification 

regarding how the requirements are 

different between the requirements in 

the proposed AD and the requirements 

mandated by AD 2014–08–11. The 

applicability of the proposed AD 

includes certain The Boeing Company 

Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes, line 

numbers 1 through 3526 inclusive. The 

applicability of AD 2014–08–11 

includes certain The Boeing Company 

Model 737–600, –700, –700C, –800, 

–900, and –900ER series airplanes, line 

numbers 1423 through 3526 inclusive. 

Although certain airplane line numbers 

are included in the applicability of both 

the proposed AD and AD 2014–08–11, 

the issues addressed by the NPRM and 

AD 2014–08–11 are not the same. 

Furthermore, the inspection instructions 

in the service information required for 

accomplishing the actions in the 

proposed AD are different from the 

inspection instructions in the service 

information required by AD 2014–08– 

11. The inspections in the proposed AD 

focus on chrome damage and corrosion 

on the shank of the forward trunnion 

pins, and the inspections required by 

AD 2014–08–11 focus on finish 

scratches and corrosion in the transition 

radius of the forward trunnion pins. We 

have not changed this AD regarding this 

issue. 

In addition, we note that the service 

information required to do the actions 

required by AD 2014–08–11 (which 

cites Boeing Special Attention Service 

Bulletin 737–32–1402, Revision 1, dated 

February 7, 2013), includes a 

recommendation by Boeing that 

operators accomplish the specified 

actions concurrently with the actions 

specified in Boeing Special Attention 

Service Bulletin 737–32–1448 (Boeing 

Special Attention Service Bulletin 737– 

32–1448, Revision 1, dated May 29, 

2015, is the appropriate source of 

service information for accomplishing 

the actions required by this AD). 


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Likewise, Boeing Special Attention 

Service Bulletin 737–32–1448, Revision 

1, dated May 29, 2015, includes a 

recommendation by Boeing that 

operators accomplish the specified 

actions concurrently with the actions 

specified in Boeing Special Attention 

Service Bulletin 737–32–1402. 

Request for Clarification of Lube 

Fittings Location 

DAL requested clarification regarding 

the location of the lube fittings for the 

forward and aft MLG trunnion pin 

assemblies in paragraph (g) of the 

NPRM. DAL commented that the NPRM 

stated to do the repetitive lubrication 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. DAL noted that Work Package 1 

of the Accomplishment Instructions of 

Boeing Special Attention Service 

Bulletin 737–32–1448, Revision 1, dated 

May 29, 2015, refers to section 12–21– 

11 of the Boeing 737–600/700/800/900 

Aircraft Maintenance Manual (AMM) as 

an accepted procedure for the repetitive 

lubrication of the MLG trunnion pin 

assemblies. DAL stated that section 12– 

21–11 of the AMM specifically 

identifies the locations of the trunnion 

bearing housing and the aft trunnion 

bearing, but does not specifically 

identify the locations of the two lube 

fittings for the forward and aft trunnion 

pins. 

We agree with the commenter that the 

two lube fittings for the forward and aft 

trunnion pins are not specifically 

mentioned in section 12–21–11 of the 

Boeing 737–600/700/800/900 AMM. 

These locations are identified as Item 

[6], ‘‘Outer Cylinder,’’ on page 307 of 

the AMM. However, there are only three 

lube fittings associated with Item [6], so 

it is possible to determine which two 

fittings are to be used for lubricating the 

forward and aft trunnion pins. We 

consulted with Boeing and confirmed 

that the two lube fittings are located on 

the bottom of the outer cylinder 

trunnion, directly under the pins. We 

have not changed this AD regarding this 

issue. 

Request for Clarification of Corrective 

Actions in Paragraph (h) of the 

Proposed AD 

DAL requested clarification of certain 

corrective actions in paragraph (h) of the 

proposed AD. DAL asked if an operator 

can replace an affected trunnion pin 

assembly instead of overhauling it. DAL 

pointed out that neither the NPRM nor 

Boeing Special Attention Service 

Bulletin 737–32–1448, Revision 1, dated 

May 29, 2015, specify the part number 

of the replacement trunnion pin 

assembly. DAL asked if an operator can 

replace an affected pin assembly with 

any properly approved pin assembly 

using the Boeing 737 Aircraft Illustrated 

Parts Catalog, Boeing Drawing 

161A0002, ‘‘Boeing Model 737–NG 

Main Landing Gear Component 

Interchangeability List,’’ or a similar 

document. 

We agree with the commenter’s 

request for clarification. Operators may 

elect to replace a trunnion pin assembly 

with a serviceable unit in lieu of 

performing an overhaul. However, 

operators should be aware that some of 

the existing trunnion pin assemblies 

require modification. Figures 9, 11, and 

12 of Boeing Special Attention Service 

Bulletin 737–32–1448, Revision 1, dated 

May 29, 2015, provide instructions for 

modifying certain pin assemblies. Note 

(c) in each of these figures refers to 

paragraph 2.C.3., ‘‘Parts Modified and 

Reidentified,’’ of Boeing Special 

Attention Service Bulletin 737–32– 

1448, Revision 1, dated May 29, 2015, 

which shows the existing and modified 

part numbers. For use of other part 

numbers, such as those identified in the 

Boeing 737 Aircraft Illustrated Parts 

Catalog or Boeing Drawing 161A0002, 

‘‘Boeing Model 737–NG Main Landing 

Gear Component Interchangeability 

List,’’ operators may request an 

alternative method of compliance in 

accordance with the procedures 

specified in paragraph (m) of this AD. 

We have not changed this AD regarding 

this issue. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM. 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

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 

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. 

Costs of Compliance 

We estimate that this AD affects 1,023 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this 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 $173,910, 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 airplanes).

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). 


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We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this 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 

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 

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 adding 

the following new airworthiness 

directive (AD): 

2016–18–01 The Boeing Company: 

Amendment 39–18631; Docket No. 

FAA–2015–8133; Directorate Identifier 

2015–NM–101–AD. 

(a) Effective Date 

This AD is effective October 5, 2016. 

(b) Affected ADs 

None. 

(c) Applicability 

(1) 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. 

(2) Installation of Supplemental Type 

Certificate (STC) ST00830SE (http://

rgl.faa.gov/Regulatory_and_Guidance_

Library/rgstc.nsf/0/184DE9A71EC3FA55862

57EAE00707DA6?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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 32, Landing Gear. 

(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 (MLGs). 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 the 

actions specified in 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 inspection 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. 


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59834 Federal Register / Vol. 81, No. 169 / Wednesday, August 31, 2016 / Rules and Regulations 

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 of 

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)(1) of this AD. Information may 

be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair, 

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) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

paragraphs (o)(3) and (o)(4) of this AD. 

(o) 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) Boeing Special Attention Service 

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

29, 2015. 

(ii) Reserved. 

(3) 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. 

(4) 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. 

(5) 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 August 

18, 2016. 

Dorr M. Anderson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2016–20686 Filed 8–30–16; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2016–9047; Directorate 

Identifier 2016–NM–092–AD; Amendment 

39–18632; AD 2016–18–02] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 777–200 

and –300ER series airplanes. This AD 

requires replacing the low-pressure 

oxygen flex hoses with new nonconductive low-pressure oxygen flex 

hoses in the gaseous passenger oxygen 

system in airplanes equipped with 

therapeutic oxygen. This AD was 

prompted by a determination that the 

low-pressure oxygen flex hoses in the 

gaseous passenger oxygen system can 

potentially be conductive. We are 

issuing this AD to prevent electrical 

current from passing through the lowpressure oxygen flex hoses in the 

gaseous passenger oxygen system, 

which can cause the flex hoses to melt 

or burn, and a consequent oxygen-fed 

fire in the passenger cabin. 

DATES: This AD is effective September 

15, 2016. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 15, 2016]. 

We must receive comments on this 

AD by October 17, 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 final rule, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 


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