Federal Register / Vol. 79, No. 17 / Monday, January 27, 2014 / Rules and Regulations 4269 

(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 Fort Worth, Texas, on January 2, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–00837 Filed 1–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0095; Directorate 

Identifier 2011–NM–197–AD; Amendment 

39–17699; AD 2013–25–03] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directives (ADs) AD 

2000–17–05 and AD 2001–04–09 for all 

the Boeing Company Model 767 

airplanes. AD 2000–17–05 required a 

functional check of the shear rivets in 

all six elevator power control actuator 

(PCA) bellcrank assemblies to determine 

the condition of the shear rivets; and 

replacement or rework of the bellcrank 

assemblies, if necessary. AD 2001–04– 

09 required repetitive testing of the 

elevator control system to determine if 

an elevator PCA is rigged incorrectly 

due to yielded or failed shear rivets in 

a bellcrank assembly for the elevator 

PCA, and follow-on actions if necessary. 

Since we issued ADs 2000–17–05 and 

2001–04–09, a terminating modification 

has been designed. This new AD 

requires an inspection to determine the 

part numbers and condition of the 

bellcrank assemblies; modification or 

replacement of the PCA bellcrank 

assembly, if necessary; and a repetitive 

functional test and mis-rig check, and 

corrective actions if necessary. We are 

issuing this AD to prevent continued 

operation with yielded or failed shear 

rivets in the elevator PCA bellcrank 

assemblies, and to prevent certain 

failures or jams in the elevator system 

from causing a hardover of the elevator 

surface, resulting in a significant pitch 

upset and possible loss of control of the 

airplane. 

DATES: This AD is effective March 3, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of March 3, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 28, 2007 (72 FR 

67236, November 28, 2007). 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of March 20, 2001 (66 FR 

13227, March 5, 2001). 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

this AD as of September 11, 2000 (65 FR 

51754, August 25, 2000). 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may view 

this referenced service information at 

the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., 

Renton, WA. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; 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: 

Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, ANM– 

130S, FAA, Seattle Aircraft Certification 

Office, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6418; 

fax: 425–917–6590; email: 

marie.hogestad@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2000–17–05, 

Amendment 39–11879 (65 FR 51754, 

August 25, 2000); and AD 2001–04–09, 

Amendment 39–12128 (66 FR 13227, 

March 5, 2001). ADs 2000–17–05 and 

2001–04–09 applied to the specified 

products. The NPRM published in the 

Federal Register on February 26, 2013 

(78 FR 12991). The NPRM proposed to 

continue to require a functional check of 

the shear rivets in all six PCA bellcrank 

assemblies to determine the condition of 

the shear rivets; and replacement or 

rework of the bellcrank assemblies, if 

necessary. The NPRM also proposed to 

continue to require repetitive testing of 

the elevator control system to determine 

if an elevator PCA is rigged incorrectly 

due to failed shear rivets in a bellcrank 

assembly of the elevator PCA, and 

follow-on actions if necessary. The 

NPRM also proposed to require an 

inspection to determine the part 

numbers and condition of the bellcrank 

assemblies; modification or replacement 

of the PCA bellcrank assembly, if 

necessary; and a repetitive functional 

test and mis-rig check, and corrective 

actions if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 12991, 

February 26, 2013) and the FAA’s 

response to each comment. 

Request To Withdraw the NPRM (78 FR 

12991, February 26, 2013) 

United Airlines (UAL) requested that 

we withdraw the NPRM (78 FR 12991, 

February 26, 2013). UAL stated that 

there may be no benefit to superseding 

AD 2001–04–09, Amendment 39–12128 

(66 FR 13227, March 5, 2001), because 

current actions provide an equivalent 

level of safety. UAL stated that, as an 

alternative method of compliance 

(AMOC) to AD 2001–04–09, it is 

presently accomplishing the actions 

described in the following service 

bulletins. UAL stated that it is 

effectively complying with the NPRM, 

and indicated other airlines may be as 

well. 

• Boeing Service Bulletin 767–27– 

0186, dated June 25, 2007. 

• Boeing Service Bulletin 767–27– 

0187, dated June 25, 2007. 

• Boeing Service Bulletin 767–27– 

0200, dated June 25, 2007. 

• Boeing Service Bulletin 767–27– 

0201, dated June 27, 2007. 

• Boeing Service Bulletin 767–27– 

0202, Revision 1, dated February 21, 

2008. 


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• Boeing Service Bulletin 767–27– 

0203, Revision 1, dated February 21, 

2008. 

We disagree with the commenter’s 

request to withdraw the NPRM (78 FR 

12991, February 26, 2013). AD 2000– 

17–05, Amendment 39–11879 (65 FR 

51754, August 25, 2000), and AD 2001– 

04–09, Amendment 39–12128 (66 FR 

13227, March 5, 2001), were considered 

interim actions. This final rule specifies 

a terminating modification that will 

further reduce the probability of the 

unsafe condition identified in those 

ADs, which includes installation of 

solid elevator PCA bellcranks or 

bellcranks with solid rivets. In addition 

to this terminating modification, this 

final rule requires new repetitive testing 

of the modified system, including 

repetitive testing of the elevator PCA 

input rod assemblies (pogo check) and 

repetitive checks of the elevator PCA 

rigging. 

As UAL indicated, we approved 

accomplishment of the service 

information required by this final rule 

as AMOCs to accomplishing the 

repetitive testing required by paragraph 

(a) of AD 2001–04–09, Amendment 39– 

12128 (66 FR 13227, March 5, 2001). 

These were global AMOCs; therefore, 

we have no way of determining the level 

of airline incorporation. Airlines similar 

to UAL, which are presently 

accomplishing the actions described in 

Boeing Service Bulletins 767–27–0186, 

767–27–0187, and 767–27–0200, all 

dated June 25, 2007; 767–27–0201, 

dated June 27, 2007; and 767–27–0202 

and 767–27–0203, both Revision 1, both 

dated February 21, 2008; as applicable; 

as AMOCs to AD 2001–04–09, can take 

credit for work already accomplished as 

specified in paragraph (f) of this final 

rule and are already doing the repetitive 

actions required by this AD. No change 

has been made to this final rule in this 

regard. 

Request To Allow Credit for Previous 

Actions 

Boeing requested that we provide 

credit for the actions required by 

paragraph (j) of the NPRM (78 FR 12991, 

February 26, 2013), if those actions were 

performed before the effective date of 

this AD using Boeing Service Bulletin 

767–27–0186 or 767–27–0187, both 

dated June 25, 2007, and it is shown 

that the service information has been 

incorporated by doing a records check. 

We find that clarification is necessary. 

Paragraph (f) of this AD states to comply 

with this AD within the compliance 

times specified, unless already done. 

For paragraph (j) of this AD, there is no 

more work required for operators who 

have already accomplished the actions 

in Boeing Service Bulletin 767–27–0186 

or 767–27–0187, both dated June 25, 

2007. No change has been made to this 

final rule in this regard. 

Request To Insert a Phrase in 

Paragraph (k)(1) of the NPRM (78 FR 

12991, February 26, 2013) 

ABX Air (ABX) requested that 

paragraph (k)(1) of the NPRM (78 FR 

12991, February 26, 2013) be revised by 

inserting the phrase, ‘‘Unless the 

function check (pogo check) specified 

by paragraph (k)(2) of this AD was 

previously accomplished.’’ ABX stated 

that paragraph (k)(1) of the NPRM 

proposed to require accomplishment of 

the pogo check in accordance with 

Boeing Service Bulletin 767–27–0186, 

dated June 25, 2007, before further flight 

after doing the inspection and 

applicable corrective actions proposed 

by paragraph (j) of the NPRM. ABX 

stated that if the pogo check was 

accomplished previously in accordance 

with Boeing Service Bulletin 767–27– 

0200, dated June 25, 2007, then the pogo 

check proposed by paragraph (k)(1) of 

the NPRM is not necessary. 

ABX further stated that the pogo 

check specified in Boeing Service 

Bulletins 767–27–0186 and 767–27– 

0200, both dated June 25, 2007, are 

equivalent, and if each input control rod 

assembly passed the pogo check 

inspection, or was overhauled or 

replaced in accordance with paragraph 

(k)(2) of the NPRM (78 FR 12991, 

February 26, 2013), then the repetitive 

pogo check limit of 12,000 flight hours 

will provide protection against input 

control rod assembly malfunction. ABX 

stated that requiring accomplishment of 

the pogo check concurrently with the 

bellcrank assembly inspection/

modification will provide no safety 

benefit if the inspections specified in 

paragraph (k)(2) of the NPRM are in 

place. 

We disagree with revising paragraph 

(k)(1) of this final rule as requested. 

Boeing Service Bulletins 767–27–0186 

and 767–27–0187, both dated June 25, 

2007 (referenced in paragraph (j) of this 

AD), are applicable to line numbers 1 

through 901. An equivalent change was 

made during production for line 

numbers 902 and subsequent. As ABX 

stated, Boeing Service Bulletins 767– 

27–0186 and 767–27–0187, both dated 

June 25, 2007, include the same testing 

provided in Boeing Service Bulletins 

767–27–0200, dated June 25, 2007; 767– 

27–0201, dated June 27, 2007; and 767– 

27–0202 and 767–27–0203, both 

Revision 1, both dated February 21, 

2008. 

However, for line numbers 1 through 

901, the initial checks (pogo and misrig) must be completed following the 

modification of the system and must be 

repeated at the repetitive inspection 

intervals provided in paragraphs (k)(2) 

and (l)(2) of this AD. Since paragraphs 

(k)(1) and (l)(1) of this AD are the initial 

checks for these airplanes, and the 

intent is to do all of the actions 

specified in Boeing Service Bulletins 

767–27–0186 and 767–27–0187, both 

dated June 25, 2007, at the time of 

modification, we disagree with making 

the requested change. No change has 

been made to this final rule in this 

regard. 

Request To Add Exception to Service 

Information 

Boeing requested that we add an 

exception to allow operators to omit 

Step 5 of Work Packages 1 and 2 of 

Boeing Service Bulletins 767–27–0186 

and 767–27–0187, both dated June 25, 

2007. Boeing stated that Step 4 of Work 

Packages 1 and 2 of Boeing Service 

Bulletins 767–27–0186 and 767–27– 

0187, both dated June 25, 2007, states 

‘‘Install elevator PCA input linkage. 

Refer to 767 AMM 27–31–06 as an 

accepted procedure.’’ Boeing stated that 

AMM 27–31–06 of the Boeing Aircraft 

Maintenance Manual requires 

adjustment of the PCA input rods per 

Task 27–31–00, which adjusts the input 

rods for each elevator PCA to make sure 

that the elevator aligns to the index 

plate. Boeing stated that Step 5 of Work 

Packages 1 and 2 of Boeing Service 

Bulletins 767–27–0186 and 767–27– 

0187, both dated June 25, 2007, states, 

‘‘Do the elevator PCA Mis-Rig test. Refer 

to 767 AMM 27–31–00 as an accepted 

procedure.’’ Boeing stated that the PCA 

input rod adjustment per AMM 27–31– 

00 is a precise rigging of the elevator 

PCA input rods. Boeing stated that a 

subsequent mis-rig test, which tests for 

a gross mis-rig of the system, is 

redundant and has no effect on 

correcting the unsafe condition. 

We agree with adding an exception in 

this final rule as requested. We redesignated paragraph (n) of the NPRM 

(78 FR 12991, February 26, 2013) as 

paragraph (n)(1) of this final rule. We 

also added new paragraph (n)(2) to this 

final rule to specify that for airplanes on 

which an adjustment of the PCA input 

rods has been done as specified in AMM 

27–31–00 of the Boeing 767 Aircraft 

Maintenance Manual during the 

accomplishment of Step 3.B.4 of Work 

Packages 1 and 2 of Boeing Service 

Bulletins 767–27–0186 and 767–27– 

0187, both dated June 25, 2007, Step 

3.B.5 of Work Packages 1 and 2 of 

Boeing Service Bulletins 767–27–0186 

and 767–27–0187, both dated June 25, 

2007, is not required. We have also 


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added a reference to paragraph (n)(2) in 

paragraph (l)(1) of this final rule. 

Clarification of NPRM (78 FR 12991, 

February 26, 2013) 

The preamble of the NPRM (78 FR 

12991, February 26, 2013) included a 

table identifying revised paragraph 

identifiers. The second line of the table 

stated that paragraph (b) of AD 2000– 

17–05, Amendment 39–11879 (65 FR 

51754, August 25, 2000), corresponds to 

paragraph (g)(4) of the NPRM. We did 

not retain paragraph (b) of AD 2000–17– 

05; therefore, there is no corresponding 

paragraph (g)(4) in the NPRM. Since this 

table is not included in the final rule, no 

change has been made to this final rule 

in this regard. 

Additional Change Made to This AD 

Certain text in paragraph (h) of the 

NPRM (78 FR 12991, February 26, 2013) 

has been redesignated as Note 1 to 

paragraph (h) in this final rule, since 

that text is explanatory only. 

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 (78 FR 

12991, February 26, 2013) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (78 FR 12991, 

February 26, 2013). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Costs of Compliance 

We estimate that this AD affects 415 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost U.S. 

Airplanes Cost per product Cost on U.S. operators 

Functional check of the shear rivets 

(actions retained from AD 2000– 

17–05, Amendment 39–11879 (65 

FR 51754, August 25, 2000)).

4 work-hours × $85 per 

hour = $340.

$0 330 $340 .............................. $112,200. 

Repetitive inspection of bellcrank assemblies (actions retained from 

AD 2001–04–09, Amendment 39– 

12128 (66 FR 13227, March 5, 

2001)).

2 work-hours × $85 per 

hour = $170 per inspection cycle.

0 335 $170 per inspection 

cycle.

$56,950 per inspection 

cycle. 

Inspection of elevator PCA bellcrank 

assemblies, functional test (pogo 

check), and elevator mis-rig check 

(new actions for Model 767 airplanes having line numbers 1– 

901).

23 work–hours × $85 

per hour = $1,955.

0 390 $1,955 ........................... $762,450. 

Repetitive functional test (pogo 

check) (new action for all Model 

767 airplanes).

32 work-hours × $85 per 

hour = $2,720 per inspection cycle.

0 415 $2,720 per inspection 

cycle.

$1,128,800 per inspection cycle. 

Repetitive elevator mis-rig check 

(new action for all Model 767 airplanes).

2 work-hours × $85 per 

hour = $170 per inspection cycle.

0 415 $170 per inspection 

cycle.

$70,550 per inspection 

cycle. 

We estimate the following costs to do 

any necessary repairs or replacements 

that will be required based on the 

results of the inspection, tests, and 

checks. We have no way of determining 

the number of aircraft that might need 

these repairs or replacements. 

We estimate that reworking the 

bellcrank assembly will take about 6 

work-hours, for a labor cost of $510 per 

airplane; however, we have no 

definitive data to determine the cost of 

parts required. We have received no 

definitive data that would enable us to 

provide a cost estimate for replacing or 

overhauling the elevator PCA input rod 

assembly, adjusting the elevator PCA 

input rod assemblies, and doing 

structural inspections specified in this 

AD. 

According to the manufacturer, some 

of the costs of this AD might 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. 

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 have determined that this AD will 

not have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 


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(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directives (ADs) 

2000–17–05, Amendment 39–11879 (65 

FR 51754, August 25, 2000); and 2001– 

04–09, Amendment 39–12128 (66 FR 

13227, March 5, 2001); and adding the 

following new AD: 

2013–25–03 the Boeing Company: 

Amendment 39–17699; Docket No. 

FAA–2013–0095; Directorate Identifier 

2011–NM–197–AD. 

(a) Effective Date 

This AD is effective March 3, 2014. 

(b) Affected ADs 

This AD supersedes AD 2000–17–05, 

Amendment 39–11879 (65 FR 51754, August 

25, 2000); and AD 2001–04–09, Amendment 

39–12128 (66 FR 13227, March 5, 2001). This 

AD affects AD 2007–24–08, Amendment 39– 

15274 (72 FR 67236, November 28, 2007). 

(c) Applicability 

This AD applies to all the Boeing Company 

Model 767–200, -300, -300F, and -400ER 

series airplanes, certificated in any category. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 27, Flight controls. 

(e) Unsafe Condition 

This AD was prompted by reports of failed 

shear rivets in the bellcrank assemblies of the 

elevator power control actuator (PCA). We 

are issuing this AD to prevent continued 

operation with yielded or failed shear rivets 

in the elevator PCA bellcrank assemblies, and 

to prevent certain failures or jams in the 

elevator system from causing a hardover of 

the elevator surface, resulting in a significant 

pitch upset and possible loss of control of the 

airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Functional Check 

This paragraph restates the requirements of 

paragraph (a) of AD 2000–17–05, 

Amendment 39–11879 (65 FR 51754, August 

25, 2000). For Model 767–200, -300, and 

-300F series airplanes, line numbers 1 

through 800 inclusive: Within 30 days after 

September 11, 2000 (the effective date AD 

2000–17–05), perform a functional check of 

one shear rivet in all six elevator PCA 

bellcrank assemblies to determine the 

condition of the shear rivets, in accordance 

with Paragraph 3 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

767–27A0166, dated August 17, 2000. Doing 

the actions required by paragraphs (j), (k), 

and (l) of this AD terminates the 

requirements of this paragraph, paragraph 

(g)(2), and paragraph (g)(3) of this AD. 

(1) If all penetration depths, when 

measured per Figure 2 of Boeing Alert 

Service Bulletin 767–27A0166, dated August 

17, 2000, are 0.50 inch or more, no further 

action is required by paragraph (g), including 

all subparagraphs, of this AD. 

(2) If any penetration depth, when 

measured per Figure 2 of Boeing Alert 

Service Bulletin 767–27A0166, dated August 

17, 2000, is 0.35 inch or more, but less than 

0.50 inch, rework or replace the bellcrank 

assembly with a new or serviceable bellcrank 

assembly within 400 flight hours after 

accomplishing the functional check. After 

installation of a new or serviceable bellcrank 

assembly, and prior to further flight, repeat 

the functional check of all the bellcrank 

assemblies to make sure the rivets are still in 

good condition (as specified in Boeing Alert 

Service Bulletin 767–27A0166, dated August 

17, 2000) after installation, in accordance 

with Figure 2 of Boeing Alert Service 

Bulletin 767–27A0166, dated August 17, 

2000. 

(3) If any penetration depth, when 

measured per Figure 2 of Boeing Alert 

Service Bulletin 767–27A0166, dated August 

17, 2000, is less than 0.35 inch, prior to 

further flight, rework or replace the bellcrank 

assembly with a new or serviceable bellcrank 

assembly. After installation of a new or 

serviceable bellcrank assembly, and prior to 

further flight, repeat the functional check of 

all the bellcrank assemblies to make sure the 

rivets are still in good condition (as specified 

in Boeing Alert Service Bulletin 767– 

27A0166, dated August 17, 2000) after 

installation, in accordance with Figure 2 of 

Boeing Alert Service Bulletin 767–27A0166, 

dated August 17, 2000. 

(h) Retained Repetitive Tests 

This paragraph restates the requirements of 

paragraph (a) of AD 2001–04–09, 

Amendment 39–12128 (66 FR 13227, March 

5, 2001), with revised provisions for 

repetitive tests. For all airplanes: Within 90 

days after March 20, 2001 (the effective date 

of AD 2001–04–09), perform a test of the 

elevator PCA bellcranks to determine if an 

elevator PCA is rigged incorrectly due to 

yielded or failed shear rivets in a bellcrank 

assembly, in accordance with Boeing Alert 

Service Bulletin 767–27A0168 (for Model 

767–200, –300, and –300F series airplanes); 

or 767–27A0169 (for Model 767–400ER series 

airplanes); both dated November 21, 2000. 

Repeat the test thereafter at least every 400 

flight hours. Doing the actions required by 

paragraphs (j), (k), and (l) of this AD 

terminates the requirements of this 

paragraph. 

Note 1 to paragraph (h) of this AD: As of 

March 20, 2001(the effective date of AD 

2001–04–09), and until the accomplishment 

of the actions required by paragraphs (j), (k), 

and (l) of this AD, as applicable, 

accomplishment of the repetitive tests 

required by paragraph (h) of this AD is 

acceptable for compliance with the 

functional check of the elevator system 

required by a certification maintenance 

requirement (CMR) that is documented as 

Item Number 27–31–00–5B in the Boeing 767 

Maintenance Planning Document (MPD), 

which is not incorporated by reference in this 

AD. After accomplishment of the actions 

required by paragraphs (j), (k), and (l) of this 

AD, accomplishment of the repetitive tests 

required by paragraph (h) of this AD are not 

acceptable for compliance with the 

functional check of the elevator system 

required by a CMR that is documented as 

Item Number 27–31–00–5B in the Boeing 767 

MPD. 

(i) Retained Follow-On Actions 

This paragraph restates the requirements of 

paragraph (b) of AD 2001–04–09, 

Amendment 39–12128 (66 FR 13227, March 

5, 2001). For all airplanes: If an elevator PCA 

is determined to be rigged incorrectly during 

any test required by paragraph (h) of this AD, 

before further flight, do a one-time inspection 

to measure penetration depth of the shear 

rivets of all three elevator bellcrank 

assemblies of the affected elevator surface, in 

accordance with Boeing Alert Service 

Bulletin 767–27A0168 (for Model 767–200, 

–300, and –300F series airplanes); or 767– 

27A0169 (for Model 767–400ER series 

airplanes); both dated November 21, 2000. 

Doing the actions required by paragraphs (j), 

(k), and (l) of this AD terminates the 

requirements of this paragraph, paragraph 

(i)(1), and paragraph (i)(2) of this AD. 

(1) If the measured penetration depth of the 

shear rivets on all bellcrank assemblies is 

0.50 inch or more: Before further flight, rerig the elevator PCA correctly, in accordance 

with Boeing Alert Service Bulletin 767– 

27A0168 (for Model 767–200, –300, and 

–300F series airplanes; or 767–27A0169 (for 

Model 767–400ER series airplanes); both 

dated November 21, 2000. 

(2) If the measured shear rivet penetration 

depth on any single bellcrank assembly is 

less than 0.50 inch: Before further flight, 

repair the bellcrank assembly by replacing 

the shear rivets or replace the bellcrank 

assembly, and reassemble and re-rig the 

elevator control system, in accordance with 

Boeing Alert Service Bulletin 767–27A0168 

(for Model 767–200, –300, and –300F series 

airplanes); or 767–27A0169 (for Model 767– 

400ER series airplanes); both dated 

November 21, 2000. 


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Federal Register / Vol. 79, No. 17 / Monday, January 27, 2014 / Rules and Regulations 4273 

(j) New Inspection and Modification 

For airplanes having line numbers 1 

through 901 inclusive: Within 72 months 

after the effective date of this AD, do a 

general visual inspection of the three PCA 

bellcrank assemblies on each elevator to 

determine the part numbers (P/Ns) of the 

bellcrank assemblies and to determine 

whether the bellcrank assembly has shear 

rivets, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–27–0186, dated June 25, 

2007 (for Model 767–200, –300, and –300F 

series airplanes); or 767–27–0187, dated June 

25, 2007 (for Model 767–400ER series 

airplanes). 

(1) If the bellcrank assembly has P/N 

252T2118–4 or 252T2118–5, and has solid 

rivets, no further action is required by this 

paragraph. 

(2) If the bellcrank is a solid one-piece 

bellcrank with no rivets, no further action is 

required by this paragraph. 

(3) If the bellcrank assembly has P/N 

252T2118–1, 252T2118–2, or 252T2118–3, 

and has shear rivets, before further flight, do 

the action specified in either paragraph 

(j)(3)(i) or (j)(3)(ii) of this AD, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–27–0186, dated 

June 25, 2007 (for Model 767–200, –300, and 

–300F series airplanes); or 767–27–0187, 

dated June 25, 2007 (for Model 767–400ER 

series airplanes); except as provided by 

paragraph (n) of this AD. 

(i) Rework the existing bellcrank to replace 

the shear rivets with solid rivets. 

(ii) Install a new, solid one-piece (no rivets) 

bellcrank assembly having P/N 252T2118–6. 

(k) New Repetitive Functional Test (Pogo 

Check) 

(1) For airplanes having line numbers 1 

through 901 inclusive: Before further flight 

after doing the inspection and applicable 

corrective actions required by paragraph (j) of 

this AD, do a functional test (pogo check) on 

each of the six elevator PCA input rod 

assemblies, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–27–0186, dated June 25, 

2007 (for Model 767–200, –300, and –300F 

series airplanes); or 767–27–0187, dated June 

25, 2007 (for Model 767–400ER series 

airplanes). 

(2) For all airplanes: At the latest of the 

times specified in paragraphs (k)(2)(i), 

(k)(2)(ii), and (k)(2)(iii) of this AD, do a 

functional test (pogo check) on each of the 

six elevator PCA input rod assemblies, in 

accordance with the Accomplishment 

Instructions of Boeing Service Bulletin 767– 

27–0200, dated June 25, 2007 (for Model 

767–200, –300, and –300F series airplanes); 

or 767–27–0201, dated June 27, 2007 (for 

Model 767–400ER series airplanes). Repeat 

the pogo check thereafter at intervals not to 

exceed 12,000 flight hours. 

(i) Before the accumulation of 12,000 total 

flight hours. 

(ii) Within 12,000 flight hours after 

completion of the most recent pogo check. 

(iii) Within 6,000 flight hours after the 

effective date of this AD. 

(3) If any elevator PCA input rod assembly 

fails to meet any functional test requirement 

of this AD, before further flight, replace the 

elevator PCA input rod assembly with a new 

or serviceable assembly, or overhaul the 

elevator PCA input rod assembly, in 

accordance with the applicable service 

information identified in paragraphs (k)(3)(i) 

and (k)(3)(ii) of this AD, except as provided 

by paragraph (n) of this AD. 

(i) For replacing or overhauling the 

assembly on Model 767–200, –300, and 

–300F airplanes: Use Boeing Service Bulletin 

767–27–0186, dated June 25, 2007; or 767– 

27–0200, dated June 25, 2007; as applicable. 

(ii) For replacing or overhauling the 

assembly on Model 767–400ER airplanes: 

Use Boeing Service Bulletin 767–27–0187, 

dated June 25, 2007; or 767–27–0201, dated 

June 27, 2007; as applicable. 

(l) New Elevator PCA Check (Mis-rig Check) 

(1) Except as provided by paragraph (n)(2) 

of this AD, for airplanes having line numbers 

1 through 901 inclusive: Before further flight 

after doing the actions required by 

paragraphs (j) and (k) of this AD, do a check 

of the elevator PCA rigging, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–27–0186, dated 

June 25, 2007 (for Model 767–200, –300, and 

–300F series airplanes); or 767–27–0187, 

dated June 25, 2007 (for Model 767–400ER 

series airplanes). 

(2) For all airplanes: At the latest of the 

times specified in paragraphs (l)(2)(i), 

(l)(2)(ii), and (l)(2)(iii) of this AD, do a check 

of the elevator PCA rigging, in accordance 

with the Accomplishment Instructions of 

Boeing Service Bulletin 767–27–0202, 

Revision 1, dated February 21, 2008 (for 

Model 767–200, –300, and –300F series 

airplanes); or 767–27–0203, Revision 1, dated 

February 21, 2008 (for Model 767–400ER 

series airplanes). Repeat the mis-rig check 

thereafter at intervals not to exceed 6,000 

flight hours. 

(i) Before the accumulation 6,000 total 

flight hours. 

(ii) Within 6,000 flight hours after the 

completion of the most recent mis-rig check, 

or after completion of the most recent 

bellcrank repetitive check, as specified in 

Boeing Alert Service Bulletin 767–27A0168, 

dated November 20, 2000. 

(iii) Within 6,000 flight hours after the 

effective date of this AD. 

(3) If a mis-rig condition is found, before 

further flight, adjust the PCA input rod 

assemblies and do a structural inspection for 

damage, in accordance with the 

Accomplishment Instructions of Boeing 

Service Bulletin 767–27–0202, Revision 1, 

dated February 21, 2008 (for Model 767–200, 

–300, and –300F airplanes); or 767–27–0203, 

Revision 1, dated February 21, 2008 (for 

Model 767–400ER airplanes). If any damage 

is found during any structural inspection, 

before further flight, repair in accordance 

with a method approved by the Manager, 

Seattle Aircraft Certification Office (ACO), 

FAA. 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. 

(m) Terminating Action 

Accomplishment of the requirements of 

paragraphs (j), (k), and (l) of this AD 

terminates the requirements of paragraphs 

(g), (h), and (i) of this AD. 

(n) Service Bulletin Exceptions 

(1) Where Boeing Service Bulletins 767– 

27–0186 and 767–27–0187, both dated June 

25, 2007, specify the use of grease BMS 3– 

24, this AD allows the alternate use of grease 

BMS 3–33. 

(2) For airplanes on which an adjustment 

of the PCA input rods has been done as 

specified in Boeing 767 AMM 27–31–00 

during the accomplishment of Step 3.B.4 of 

Work Packages 1 and 2 of Boeing Service 

Bulletins 767–27–0186 and 767–27–0187, 

both dated June 25, 2007: Accomplishment of 

the actions specified in Step 3.B.5 of Work 

Package 1 and 2 of Boeing Service Bulletins 

767–27–0186 and 767–27–0187, both dated 

June 25, 2007, is not required by this AD. 

(o) Method of Compliance for Paragraph (k) 

of AD 2007–24–08, Amendment 39–15274 

(72 FR 67236, November 28, 2007) 

For airplanes identified in paragraphs 

(o)(1) and (o)(2) of this AD: Doing the actions 

required by paragraphs (j), (k), and (l) of this 

AD is acceptable for compliance with the 

actions required by paragraph (k) of AD 

2007–24–08, Amendment 39–15274 (72 FR 

67236, November 28, 2007). 

(1) Group 1, Configuration 2, airplanes 

identified in Boeing Special Attention 

Service Bulletin 767–27–0197, Revision 1, 

dated July 19, 2007. 

(2) Group 1, Configuration 1, airplanes 

identified in Boeing Special Attention 

Service Bulletin 767–27–0198, Revision 1, 

dated July 19, 2007. 

(p) Parts Installation Prohibition 

As of the effective date of this AD, no 

person may install a bellcrank assembly, P/ 

N 252T2118–1, 252T2118–2, or 252T2118–3, 

on any airplane. 

(q) Credit for Previous Actions 

This paragraph provides credit for the 

actions required by paragraph (l) of this AD, 

if those actions were performed before the 

effective date of this AD using Boeing Service 

Bulletin 767–27–0202 (for Model 767–200, 

–300, and –300F airplanes); or 767–27–0203 

(for Model 767–400ER airplanes); both dated 

June 25, 2007, which are not incorporated by 

reference in this AD. 

(r) 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 (s) 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. 


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4274 Federal Register / Vol. 79, No. 17 / Monday, January 27, 2014 / Rules and Regulations 

(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) AMOCs approved previously for AD 

2001–04–09, Amendment 39–12128 (66 FR 

13227, March 5, 2001), are approved as 

AMOCs for the corresponding requirements 

of this AD. 

(s) Related Information 

(1) For more information about this AD, 

contact Marie Hogestad, Aerospace Engineer, 

Systems and Equipment Branch, ANM–130S, 

FAA, Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 98057– 

3356; phone: 425–917–6418; fax: (425) 917– 

6590; email: marie.hogestad@faa.gov. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD may be obtained at the addresses 

specified in paragraphs (t)(7) and (t)(8) of this 

AD. 

(t) 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. 

(3) The following service information was 

approved for IBR on March 3, 2014. 

(i) Boeing Service Bulletin 767–27–0186, 

dated June 25, 2007. 

(ii) Boeing Service Bulletin 767–27–0187, 

dated June 25, 2007. 

(iii) Boeing Service Bulletin 767–27–0200, 

dated June 25, 2007. 

(iv) Boeing Service Bulletin 767–27–0201, 

dated June 27, 2007. 

(v) Boeing Service Bulletin 767–27–0202, 

Revision 1, dated February 21, 2008. 

(vi) Boeing Service Bulletin 767–27–0203, 

Revision 1, dated February 21, 2008. 

(4) The following service information was 

approved for IBR on November 28, 2007 (72 

FR 67236, November 28, 2007). 

(i) Boeing Special Attention Service 

Bulletin 767–27–0197, Revision 1, dated July 

19, 2007. 

(ii) Boeing Special Attention Service 

Bulletin 767–27–0198, Revision 1, dated July 

19, 2007. 

(5) The following service information was 

approved for IBR on March 20, 2001 (66 FR 

13227, March 5, 2001). 

(i) Boeing Alert Service Bulletin 767– 

27A0168, dated November 21, 2000. 

(ii) Boeing Alert Service Bulletin 767– 

27A0169, dated November 21, 2000. 

(6) The following service information was 

approved for IBR on September 11, 2000 (65 

FR 51754, August 25, 2000). 

(i) Boeing Alert Service Bulletin 767– 

27A0166, dated August 17, 2000. 

(ii) Reserved. 

(7) 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. 

(8) 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. 

(9) 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 

December 4, 2013. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–01433 Filed 1–24–14; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Parts 52 and 70 

[EPA–R07–OAR–2013–0765; FRL–9905–66– 

Region–7] 

Approval and Promulgation of 

Implementation Plans; State of 

Kansas; Annual Emissions Fee and 

Annual Emissions Inventory 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Direct final rule. 

SUMMARY: The Environmental Protection 

Agency (EPA) is taking direct final 

action to approve a revision to the 

Kansas State Implementation Plan (SIP) 

and Operating Permits Program. EPA is 

approving a revision to the Kansas rule 

entitled ‘‘Annual Emissions Fee.’’ These 

revisions align the State’s reporting 

requirements with the Federal Air 

Emissions Reporting Requirements Rule 

(AERR). 

DATES: This direct final rule will be 

effective on March 28, 2014, without 

further notice, unless EPA receives 

adverse comment by February 26, 2014. 

If EPA receives adverse comment, we 

will publish a timely withdrawal of the 

direct final rule in the Federal Register 

informing the public that the rule will 

not take effect. 

ADDRESSES: Submit your comments, 

identified by Docket ID No. EPA–R07– 

OAR–2013–0765, by one of the 

following methods: 

1. www.regulations.gov. Follow the 

on-line instructions for submitting 

comments. 

2. Email: kemp.lachala@epa.gov 

3. Mail or Hand Delivery: Lachala 

Kemp, Environmental Protection 

Agency, Air Planning and Development 

Branch, 11201 Renner Boulevard, 

Lenexa, Kansas 66219. 

Instructions: Direct your comments to 

Docket ID No. EPA–R07–OAR–2013– 

0765. EPA’s policy is that all comments 

received will be included in the public 

docket without change and may be 

made available online at 

www.regulations.gov, including any 

personal information provided, unless 

the comment includes information 

claimed to be Confidential Business 

Information (CBI) or other information 

whose disclosure is restricted by statute. 

Do not submit through 

www.regulations.gov or email 

information that you consider to be CBI 

or otherwise protected. The 

www.regulations.gov Web site is an 

‘‘anonymous access’’ system, which 

means EPA will not know your identity 

or contact information unless you 

provide it in the body of your comment. 

If you send an email comment directly 

to EPA without going through 

www.regulations.gov, your email 

address will be automatically captured 

and included as part of the comment 

that is placed in the public docket and 

made available on the Internet. If you 

submit an electronic comment, EPA 

recommends that you include your 

name and other contact information in 

the body of your comment and with any 

disk or CD–ROM you submit. If EPA 

cannot read your comment due to 

technical difficulties and cannot contact 

you for clarification, EPA may not be 

able to consider your comment. 

Electronic files should avoid the use of 

special characters, any form of 

encryption, and be free of any defects or 

viruses. 

Docket: All documents in the docket 

are listed in the www.regulations.gov 

index. Although listed in the index, 

some information is not publicly 

available, i.e., CBI or other information 

whose disclosure is restricted by statute. 

Certain other material, such as 

copyrighted material, will be publicly 

available only in hard copy form. 

Publicly available docket materials are 

available either electronically in 

www.regulations.gov or in hard copy at 

the Environmental Protection Agency, 

Air Planning and Development Branch, 

11201 Renner Boulevard, Lenexa, 

Kansas 66219. The Regional Office’s 

official hours of business are Monday 

through Friday, 8:00 to 4:30 excluding 

Federal holidays. The interested persons 

wanting to examine these documents 

should make an appointment with the 

office at least 24 hours in advance. 


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