42014 Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations 

the lubrication and functional check are 

specified in paragraphs (i)(1) and (i)(2) of this 

AD. 

(1) For airplanes identified in paragraphs 

(c)(1) and (c)(2) of this AD that are not 

identified in paragraph (c)(3) of this AD: 

(i) The initial compliance time for the 

lubrication of the inboard elevator hinge 

bearings is within 18 months after the most 

recent lubrication. The repetitive lubrication 

intervals are specified in Item Number 27– 

CMR–10, ‘‘Lubricate inboard elevator hinge 

bearings,’’ of Section G., ‘‘CMR Tasks,’’ of the 

Boeing 747–8/8F Certification Maintenance 

Requirements (CMRs) Document D011U721– 

02–03, Revision December 2013. 

(ii) The initial compliance time for the 

functional check of the inboard elevator 

hinge bearing and power control unit rod end 

bearing freeplay is within 12 months after the 

effective date of this AD. The repetitive 

functional check intervals are specified in 

Item Number 27–CMR–11, ‘‘Functional check 

of inboard elevator hinge bearing and power 

control unit rod end bearing free play,’’ of 

Section G., ‘‘CMR Tasks,’’ of the Boeing 747– 

8/8F Certification Maintenance 

Requirements, D011U721–02–03, Revision 

December 2013. 

(2) For airplanes identified in paragraph 

(c)(3) of this AD: 

(i) The initial compliance time for the 

lubrication of the inboard elevator hinge 

bearings is within 24 months after the most 

recent lubrication. Repeat the lubrication 

thereafter at intervals not to exceed 24 

months. 

(ii) The initial compliance time for the 

functional check of the inboard elevator 

hinge bearing and power control unit rod end 

bearing freeplay is within 36 months after the 

effective date of this AD. Repeat the 

functional check thereafter at intervals not to 

exceed 36 months. 

(j) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install on any airplane an LCE 

having part number (P/N) CA49253–001 or 

CA49253–002, or an inboard elevator PCP 

having P/N 327400–1009. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (h) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Alert 

Service Bulletin 747–27A2513, dated 

February 4, 2014, which is not incorporated 

by reference in this AD. 

(l) 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 (m)(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 

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. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) For service information that contains 

steps that are labeled as Required for 

Compliance (RC), the provisions of 

paragraphs (l)(4)(i) and (l)(4)(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 

(m) Related Information 

(1) For more information about this AD, 

contact Douglas Tsuji, Senior Aerospace 

Engineer, Systems and Equipment Branch, 

ANM–130S, Seattle Aircraft Certification 

Office, FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6546; fax: 

425–917–6590; email: douglas.tsuji@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(n) 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 Alert Service Bulletin 747– 

27A2506, dated February 3, 2014. 

(ii) Boeing Service Bulletin 747–27A2513, 

Revision 1, dated July 18, 2014. 

(iii) Boeing 747–8/8F Certification 

Maintenance Requirements (CMRs) 

Document D011U721–02–03, Revision 

December 2013. 

(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. 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. 

(4) You may view this service information 

at 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 July 1, 

2015. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–17023 Filed 7–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0428; Directorate 

Identifier 2014–NM–067–AD; Amendment 

39–18205; AD 2015–14–07] 

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 

airplanes. This AD was prompted by 

reports of deficiencies in the flight 

control module (FCM) software. This 

AD requires installing certain FCM 

software. We are issuing this AD to 

correct deficiencies in the FCM 

software, which, if not corrected, could 

prevent continued safe flight and 

landing. 

DATES: This AD is effective August 20, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of August 20, 2015. 

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, 


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Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations 42015 

call 425–227–1221. It is also available 

on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0428. 

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– 

0428; 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 

Document 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: 

Douglas Tsuji, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, Seattle Aircraft Certification 

Office (ACO), FAA, 1601 Lind Avenue 

SW., Renton, WA 98057–3356; phone: 

425–917–6546; fax: 425–917–6590; 

email: douglas.tsuji@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 787–8 airplanes. The NPRM 

published in the Federal Register on 

July 2, 2014 (79 FR 37684). The NPRM 

was prompted by reports of deficiencies 

in the FCM software. The NPRM 

proposed to require installing certain 

FCM software. We are issuing this AD 

to correct deficiencies in the FCM 

software, which, if not corrected, could 

prevent continued safe flight and 

landing. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 37684, 

July 2, 2014) and the FAA’s response to 

each comment. 

Support for the NPRM (79 FR 37684, 

July 2, 2014) 

United Airlines Engineering, the Air 

Line Pilots Association International 

(ALPA), and Boeing expressed support 

for the NPRM (79 FR 37684, July 2, 

2014). United Airlines Engineering also 

indicated that all of its airplanes were 

modified as of April 2, 2014, with no 

adverse effects. 

Request To Issue Alternative Methods 

of Compliance (AMOCs) 

Boeing requested that we issue 

AMOCs for several items it identified in 

Boeing Alert Service Bulletin B787– 

81205–SB270020–00, Issue 001, dated 

February 6, 2014. Boeing requested 

AMOCs to do the following actions. 

• Install the FCM operational 

program software (OPS) in the Mass 

Storage Device 1 only. 

• To identify the existing FCM OPS 

software as either part number HNP5E– 

AL01–5010 (Block Point 1) or part 

number HNP5F–AL01–5011 (Block 

Point 2) software. 

• To specify that the FCM loadable 

diagnostic information (LDI) database 

(DB) and FCM air data reference 

function (ADRF) DB software are not 

required to be reloaded if the FCM OPS 

software part number HNP5C–AL01– 

5012 can be successfully loaded without 

reloading the databases. 

We agree that the issues raised by the 

commenter should be addressed. The 

issues are addressed in a new revision 

to Boeing Alert Service Bulletin B787– 

81205–SB270020–00, Issue 001, dated 

February 6, 2014. We have revised 

paragraphs (c), (g), and (h) of this AD to 

reference Boeing Alert Service Bulletin 

B787–81205–SB270020–00, Issue 002, 

dated February 12, 2015, as the 

appropriate source of service 

information for accomplishing the 

required actions. There has been no 

expansion to the applicability or scope 

of this AD. Use of either Boeing Alert 

Service Bulletin B787–81205– 

SB270020–00, Issue 001, dated February 

6, 2014, or Boeing Alert Service Bulletin 

B787–81205–SB270020–00, Issue 002, 

dated February 12, 2015, is acceptable. 

No further work is necessary on 

airplanes on which operators have done 

the actions described in Boeing Alert 

Service Bulletin B787–81205– 

SB270020–00, Issue 001, dated February 

6, 2014. We have added new paragraph 

(j) of this AD to provide credit for 

actions required by paragraph (g) of this 

AD, if those actions were performed 

before the effective date of this AD using 

Boeing Alert Service Bulletin B787– 

81205–SB270020–00, Issue 001, dated 

February 6, 2014. We have re-designated 

subsequent paragraphs accordingly. 

However, we disagree with issuing 

AMOCs at this time. AMOCs provide an 

alternative method of compliance to the 

methods required to be used in the 

associated AD. An AMOC is issued only 

after an AD has been issued and only 

after data are provided to show that the 

proposed solution is complete and 

addresses the unsafe condition. 

Request To Issue an AMOC for Later 

Software Versions 

Boeing requested that we issue an 

AMOC to allow installation of the FCM 

Block Point 4 software or later FCM 

software in lieu of the FCM Block Point 

3 software proposed by the NPRM (79 

FR 37684, July 2, 2014). Boeing 

explained that the FCM Block Point 4 

software or later FCM software updates 

are an alternative to the Block Point 3 

software, and that operators may wish to 

install Block Point 4 or later FCM 

software due to the additional product 

improvements provided in the later 

software versions. 

We agree that FCM Block Point 4 (or 

later FAA-approved FCM software 

versions) includes the Block Point 3 

updates and therefore corrects the 

unsafe condition identified in this AD. 

We have retained the compliance time 

specified in paragraph (g) of the 

proposed AD (79 FR 37684, July 2, 

2014); clarified and moved the required 

software installation from paragraph (g) 

of the proposed AD to new paragraph 

(g)(1) of this AD; and added new 

paragraphs (g)(2), (g)(3), and (g)(4) of 

this AD, which specify to install FCM 

Block Point 4 in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin B787–81205– 

SB270023–00, Issue 001, dated July 24, 

2014, or to install FCM Common Block 

Point 1 in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin B787–81205– 

SB270027–00, Issue 002, dated March 9, 

2015, or to install any later FAAapproved FCM software version using a 

method approved in accordance with 

the procedures specified in paragraph 

(k) of this AD. As stated previously, an 

AMOC is issued only after an AD has 

been issued and only after data are 

provided to show that the proposed 

solution is complete and addresses the 

unsafe condition. Also, as previously 

stated, we have added new paragraph (j) 

of this AD to provide credit for actions 

required by paragraph (g) of this AD, if 

those actions were performed before the 

effective date of this AD using Boeing 

Service Bulletin B787–81205– 

SB270027–00, Issue 001, dated 

September 26, 2014. 

In addition, we recommend that 

Boeing incorporate the provision for 

later approved parts in its service 

information, when appropriate. This 

provision is described in FAA Advisory 

Circular (AC) 20–176A, dated June 16, 

2014. (See http://rgl.faa.gov/Regulatory_

and_Guidance_Library/

rgAdvisoryCircular.nsf/0/


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979ddd1479e1ec6f86257cfc0052d4e9/

$FILE/AC%2020-176A.PDF.) 

Request To Clarify the Minimum 

Concurrent Requirement 

Boeing requested that we revise 

paragraph (h) of the NPRM (79 FR 

37684, July 2, 2014) to clarify that the 

minimum concurrent requirement for 

Group 1 airplanes identified in Boeing 

Alert Service Bulletin B787–81205– 

SB270020–00, Issue 001, dated February 

6, 2014, is to install the FCM LDI DB 

software and central maintenance 

computer function (CMCF) LDI DB 

software. Boeing stated that the updated 

FCM OPS software is installed per 

Boeing Alert Service Bulletin B787– 

81205–SB270020–00, Issue 001, dated 

February 6, 2014, and therefore, the 

previous FCM OPS software version 

specified in Boeing Alert Service 

Bulletin B787–81205–SB270017–00, 

Issue 001, dated September 18, 2013, 

does not need to be installed. 

We agree with the commenter’s 

request for clarification. This 

clarification was addressed in the new 

revision of Boeing Alert Service Bulletin 

B787–81205–SB270020–00, Issue 002, 

dated February 12, 2015, which we have 

replicated in the final rule by revising 

paragraph (h) to include the statement 

‘‘. . . or at a minimum install the FCM 

LDI DB and CMCF LDI DB software, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service 

Bulletin B787–81205–SB270017–00, 

Issue 001, dated September 18, 2013. 

Request To Revise the Discussion 

Section of the NPRM (79 FR 37684, July 

2, 2014) 

Boeing requested that we revise the 

source of the deficiency provided in the 

first sentence of the Discussion section 

of the NPRM (79 FR 37684, July 2, 

2014), which stated, in part, ‘‘We have 

received reports of in-service incidents 

and identified an indicating system 

shortcoming due to. . . .’’ Boeing stated 

that the issues are with the flight control 

system, not the indicating system. 

We agree with the commenter that the 

shortcoming is in the flight control 

system, not the indicating system. 

However, this section is not repeated in 

the final rule. Therefore no change is 

needed to this AD. 

Request To Clarify Paragraph (i) of the 

Proposed AD (79 FR 37684, July 2, 

2014) 

Boeing requested that we revise 

paragraph (i) of the proposed AD (79 FR 

37684, July 2, 2014), which referred to 

installation of ‘‘new’’ software. Boeing 

requested that we remove the word 

‘‘new’’ from that sentence. Boeing stated 

that only the FCM OPS software is new, 

and that the FCM LDI DB, FCM ADRF 

DB, and CMCF LDI DB software 

identified in Boeing Alert Service 

Bulletin B787–81205–SB270020–00, 

Issue 001, dated February 6, 2014, are 

previous software versions. 

We agree with the request, for the 

reasons provided by the commenter. We 

have revised paragraph (i) of this AD 

accordingly. 

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 (79 FR 

37684, July 2, 2014) for correcting the 

unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 37684, 

July 2, 2014). 

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 

Boeing has issued the following 

service bulletins. 

• Boeing Alert Service Bulletin B787– 

81205–SB270017–00, Issue 001, dated 

September 18, 2013. This service 

information describes procedures for 

installing FCM OPS, FCM LDI DB, and 

CMCF LDI DB software, and doing a 

software configuration check. 

• Boeing Alert Service Bulletin B787– 

81205–SB270020–00, Issue 002, dated 

February 12, 2015. This service 

information describes procedures for 

installing FCM OPS, FCM LDI DB, and 

FCM ADRF DB software, and doing a 

software configuration check. 

• Boeing Service Bulletin B787– 

81205–SB270023–00, Issue 001, dated 

July 24, 2014. This service information 

describes procedures for installing FCM 

OPS, FCM LDI DB, FCM ADRF DB, and 

CMCF LDI DB software, and doing a 

software configuration check. 

• Boeing Service Bulletin B787– 

81205–SB270027–00, Issue 002, dated 

March 9, 2015. This service information 

describes procedures for installing FCM 

OPS, FCM LDI DB, FCM Compatibility 

DB, and CMCF LDI DB software, and 

doing a software configuration check. 

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 or AD. 

Costs of Compliance 

We estimate that this AD affects 11 

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 

FCM BP3 software installation ....................... 2 work-hours × $85 per hour = $170 ............. $0 $170 $1,870 

Concurrent FCM BP2 software installation 

(Group 1 airplanes).

2 work-hours × $85 per hour = $170 ............. 630 800 8,800 

According to the manufacturer, all of 

the costs of this AD may be covered 

under warranty, thereby reducing the 

cost impact on affected individuals. We 

do not control warranty coverage for 

affected individuals. As a result, we 

have included all costs in our cost 

estimate. 

The parts cost for the FCM BP3 

software installation is not included in 

our cost estimate. It is considered 

Boeing-provided loadable software, 

which is referenced in Boeing Alert 

Service Bulletin B787–81205– 

SB270020–00, Issue 002, dated February 

12, 2015, under ‘‘Parts & Materials 

Supplied by the Operator.’’ 

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 


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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): 

2015–14–07 The Boeing Company: 

Amendment 39–18205; Docket No. 

FAA–2014–0428; Directorate Identifier 

2014–NM–067–AD. 

(a) Effective Date 

This AD is effective August 20, 2015. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to The Boeing Company 

Model 787–8 airplanes, certificated in any 

category, as identified in Boeing Alert 

Service Bulletin B787–81205–SB270020–00, 

Issue 002, dated February 12, 2015. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by reports of 

deficiencies in the flight control module 

(FCM) software. We are issuing this AD to 

correct deficiencies in the FCM software, 

which, if not corrected, could prevent 

continued safe flight and landing. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) FCM Software Installation 

Within 6 months after the effective date of 

this AD: Do the actions specified in 

paragraph (g)(1), (g)(2), (g)(3), or (g)(4) of this 

AD. 

(1) Use the onboard data load function 

(ODLF) to install FCM Block Point 3 software 

(including FCM operational program 

software (OPS), FCM loadable diagnostic 

information (LDI) database (DB) software, 

and FCM air data reference function (ADRF) 

DB software), in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin B787–81205–SB270020–00, 

Issue 002, dated February 12, 2015. 

(2) Use the ODLF to install FCM Block 

Point 4 software (including FCM OPS, FCM 

LDI DB software, FCM ADRF DB software, 

and central maintenance computer function 

(CMCF) LDI DB software), in accordance with 

the Accomplishment Instructions of Boeing 

Service Bulletin B787–81205–SB270023–00, 

Issue 001, dated July 24, 2014. 

(3) Use the ODLF to install FCM Common 

Block Point 1 software (including FMC OPS, 

FCM LDI DB software, FCM Compatibility 

DB software, and CMCF LDI DB software), in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin B787– 

81205–SB270027–00, Issue 002, dated March 

9, 2015. 

(4) Install any later FAA-approved FCM 

software version using a method approved in 

accordance with the procedures specified in 

paragraph (k) of this AD. 

(h) Concurrent Requirements 

For Group 1 airplanes, as identified in 

Boeing Alert Service Bulletin B787–81205– 

SB270020–00, Issue 002, dated February 12, 

2015: Prior to or concurrently with 

accomplishing the actions required by 

paragraph (g) of this AD, use the ODLF to 

install FCM OPS, FCM LDI DB, and CMCF 

LDI DB software, or at a minimum install the 

FCM LDI DB and CMCF LDI DB software, in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

B787–81205–SB270017–00, Issue 001, dated 

September 18, 2013. 

(i) Parts Installation Prohibition 

After installation of the software specified 

in paragraphs (g) and (h) of this AD, no 

person may install any previous versions of 

the FCM OPS, FCM LDI DB, FCM ADRF DB, 

or CMCF LDI DB software, on any airplane. 

(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 Alert Service 

Bulletin B787–81205–SB270020–00, Issue 

001, dated February 6, 2014; or Boeing 

Service Bulletin B787–81205–SB270027–00, 

Issue 001, dated September 26, 2014; which 

are 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) 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) If the service information contains steps 

that are labeled as RC (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as RC are recommended. Those steps 

that are not labeled as RC may be deviated 

from using accepted methods different from 

those identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as RC can 

be done and the airplane can be put back in 

a serviceable condition. Any substitutions or 

changes to steps labeled as RC require 

approval of an AMOC. 

(l) Related Information 

(1) For more information about this AD, 

contact Douglas Tsuji, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

Seattle Aircraft Certification Office (ACO), 

FAA, 1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6546; fax: 425– 

917–6590; email: douglas.tsuji@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference is 

available at the addresses specified in 

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

(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. 


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42018 Federal Register / Vol. 80, No. 136 / Thursday, July 16, 2015 / Rules and Regulations 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Alert Service Bulletin B787– 

81205–SB270020–00, Issue 002, dated 

February 12, 2015. 

(ii) Boeing Service Bulletin B787–81205– 

SB270023–00, Issue 001, dated July 24, 2014. 

(iii) Boeing Service Bulletin B787–81205– 

SB270027–00, Issue 002, dated March 9, 

2015. 

(iv) Boeing Alert Service Bulletin B787– 

81205–SB270017–00, Issue 001, dated 

September 18, 2013. 

(3) For Boeing 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 July 2, 

2015. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2015–17203 Filed 7–15–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2015–1177; Directorate 

Identifier 2015–CE–009–AD; Amendment 

39–18208; AD 2015–14–10] 

RIN 2120–AA64 

Airworthiness Directives; PILATUS 

AIRCRAFT LTD. Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

PILATUS AIRCRAFT LTD. Model PC– 

12/47 and PC–12/47E airplanes. This 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as the aileron trim tab 

disconnecting above 10,000 feet 

altitude. We are issuing this AD to 

require actions to address the unsafe 

condition on these products. 

DATES: This AD is effective August 20, 

2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 20, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2015– 

1177; or in person at Document 

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 service information identified in 

this AD, contact PILATUS AIRCRAFT 

LTD, Customer Support Manager, CH– 

6371 STANS, Switzerland; phone: +41 

(0)41 619 33 33; fax: +41 (0)41 619 73 

11; email: SupportPC12@pilatusaircraft.com; internet: http://

www.pilatus-aircraft.com. You may 

review this referenced service 

information at the 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. 

FOR FURTHER INFORMATION CONTACT: 

Doug Rudolph, Aerospace Engineer, 

FAA, Small Airplane Directorate, 901 

Locust, Room 301, Kansas City, 

Missouri 64106; telephone: (816) 329– 

4059; fax: (816) 329–4090; email: 

doug.rudolph@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to adding an AD that would 

apply to PILATUS AIRCRAFT LTD. 

Model PC–12/47 and PC–12/47E 

airplanes. The NPRM was published in 

the Federal Register on May 1, 2015 (80 

FR 24854). The NPRM proposed to 

correct an unsafe condition for the 

specified products and was based on 

mandatory continuing airworthiness 

information (MCAI) originated by an 

aviation authority of another country. 

The MCAI states: 

During a continued airworthiness review, a 

potential unsafe condition was identified that 

could result from a disconnected aileron trim 

tab occurring above an altitude of 10.000 feet. 

This condition, if not corrected, could lead, 

in case of a disconnection of an aileron trim 

tab, to undamped aeroplane vibrations, 

potentially resulting in structural failure. 

To address this potential unsafe condition, 

Pilatus Aircraft Ltd. issued SB No. 27–021 to 

provide instructions for replacement of the 

aileron tab counter balance weight. 

For the reason described above, this AD 

requires replacement of the aileron tab 

counter balance weight with a new, slightly 

heavier, aileron tab counter balance weight. 

The MCAI can be found in the AD 

docket on the Internet at: http://

www.regulations.gov/

#!documentDetail;D=FAA-2015-1177- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal and the FAA’s 

response to each comment. 

Request Revision of Paragraph (e) 

Reason of the AD 

Johan Kruger stated the sentence of 

paragraph (e) Reason in the proposed 

AD was incomplete and misleading: 

We are issuing this AD to prevent a 

disconnected aileron trim tab, which could 

lead to undamped airplane vibrations, 

potentially resulting in structural failure. 

Johan Kruger proposed replacing the 

above sentence with this sentence 

similar to the MCAI: 

We are issuing this AD to prevent 

undamped airplane vibrations, potentially 

resulting in structural failure in case of a 

disconnected aileron trim tab. 

We agree with the commenter that the 

proposed sentence is clarification of the 

unsafe condition. We have adopted the 

proposed sentence in paragraph (e) of 

the AD. 

Request Correction of Part Number 

(P/N) 

Johan Kruger stated the cited part 

number (P/N) 27.15.12.037 of the 

aileron trim tab assembly quoted is 

wrong in paragraphs (f)(2) and (f)(3) of 

the proposed AD; the correct P/N is 

527.15.12.037. We infer that the 

commenter requested correction of the 

incorrect P/N. 

We agree with the commenter that the 

P/N in the proposed AD is incorrect. We 

have changed the incorrect P/N to 

527.15.12.037 in paragraphs (f)(2) and 

(f)(3) of the AD. 

Request Correction of Misleading 

Wording in Paragraph (f)(4) of the AD 

Johan Kruger commented the wording 

in paragraph 2(f)(4) is misleading, ‘‘. . . 

provided that an aileron trim tab 

assembly, P/N 527.15.12.037 or 

527.15.12.038 is not installed on the 

airplane.’’ 

Johan Kruger further wrote that 

Pilatus proposed the wording be 

changed to read, ‘‘. . . provided that an 


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