Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations 45337 

(c) Effective Date 

This AD becomes effective August 20, 2014 

to all persons except those persons to whom 

it was made immediately effective by 

Emergency AD 2014–12–51, issued on June 

10, 2014, which contained the requirements 

of this AD. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Within 10 hours TIS, remove the 

horizontal stabilizer, clean the junction 

frame, and dye-penetrant inspect around the 

circumference of the junction frame for a 

crack in the areas shown in Figure 1 of 

Airbus Helicopters EC130 Emergency Alert 

Service Bulletin No. 05A017, Revision 0, 

dated June 6, 2014 (EASB 05A017). Pay 

particular attention to the area around the 4 

spars (item b) of Figure 1 of EASB 05A017. 

An example of a crack is shown in Figure 3 

of EASB 05A017. 

(2) Within 25 hours TIS of the inspection 

required by paragraph (e)(1) of this AD, and 

thereafter at intervals not exceeding 25 hours 

TIS, either perform the actions of paragraph 

(e)(1) of this AD or, if the area is clean, using 

a borescope, inspect around the 

circumference of the junction frame for a 

crack in the areas shown in Figure 2 of EASB 

05A017. Pay particular attention to the area 

around the 4 spars (item b) of Figure 2 of 

EASB 05A017. An example of a crack is 

shown in Figure 3 of EASB 05A017. 

(3) If there is a crack, before further flight, 

replace the junction frame. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Robert Grant, 

Aviation Safety Engineer, Safety Management 

Group, FAA, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone (817) 222– 

5110; email robert.grant@faa.gov. 

(2) For operations conducted under a 14 

CFR part 119 operating certificate or under 

14 CFR part 91, subpart K, we suggest that 

you notify your principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office or 

certificate holding district office, before 

operating any aircraft complying with this 

AD through an AMOC. 

(h) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency EAD No. 

2014–0145–E, dated June 6, 2014. You may 

view the EASA AD on the Internet at http:// 

www.regulations.gov in Docket No. FAA– 

2014–0515. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 5302: Rotorcraft Tailboom. 

(j) 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) Airbus Helicopters Emergency Alert 

Service Bulletin No. 05A017, Revision 0, 

dated June 6, 2014. 

(ii) [Reserved] 

(3) For Airbus Helicopters service 

information identified in this AD, contact 

Airbus Helicopters, Inc., 2701 N. Forum 

Drive, Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax (972) 

641–3775; or at http://www.air

bushelicopters.com/techpub. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(5) You may also 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 July 24, 

2014. 

Lance T. Gant, 

Acting Directorate Manager, Rotorcraft 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–18247 Filed 8–4–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0056; Directorate 

Identifier 2013–NM–160–AD; Amendment 

39–17906; AD 2014–15–04] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Saab AB, Saab Aerosystems Model 

SAAB 2000 airplanes. This AD was 

prompted by a report of rudder pedal 

restriction which was the result of water 

leakage at the inlet tubing of an in-line 

heater in the lower part of the forward 

fuselage. This AD requires deactivating 

the potable water system, or 

alternatively filling and activating the 

potable water system. We are issuing 

this AD to prevent rudder pedal 

restriction due to the pitch control 

mechanism becoming frozen as the 

result of water spray, which could 

prevent disconnection and normal pitch 

control, and consequently result in 

reduced controllability of the airplane. 

DATES: This AD becomes effective 

September 9, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 9, 2014. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://www.

regulations.gov/#!docketDetail;D=FAA2014-0056; or in person at the 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. 

For service information identified in 

this AD, contact Saab AB, Saab 

Aerosystems, SE–581 88, Linko ̈ping, 

Sweden; telephone +46 13 18 5591; fax 

+46 13 18 4874; email saab2000.tech

support@saabgroup.com; Internet 

http://www.saabgroup.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. 

FOR FURTHER INFORMATION CONTACT: 

Shahram Daneshmandi, Aerospace 

Engineer, International Branch, ANM– 

116, Transport Airplane Directorate, 

FAA, 1601 Lind Avenue SW., Renton, 

WA 98057–3356; telephone 425–227– 

1112; fax 425–227–1149. 

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 Saab AB, Saab 

Aerosystems Model SAAB 2000 

airplanes. The NPRM published in the 

Federal Register on February 25, 2014 

(79 FR 10433). The NPRM was 

prompted by a report of rudder pedal 

restriction which was the result of water 

leakage at the inlet tubing of an in-line 

heater in the lower part of the forward 

fuselage. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2013–0172R1, 

dated September 6, 2013 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

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45338 Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations 

MCAI’’), to correct an unsafe condition 

for certain Saab AB, Saab Aerosystems 

Model SAAB 2000 airplanes. The MCAI 

states: 

One occurrence of rudder pedal restriction 

has been reported on a SAAB 2000 

aeroplane. Subsequent investigation showed 

that this was the result of water leakage at the 

inlet tubing for the in-line heater (25HY) in 

the lower part of the forward fuselage (Zone 

116). The in-line heater attachment was 

found ruptured, which resulted in water 

spraying in the area. Frozen water on the 

rudder control mechanism in Zone 116 then 

led to the rudder pedal restriction. 

Analysis after the reported event indicates 

that the pitch control mechanism (including 

pitch disconnect/spring unit) may also be 

frozen as a result of water spray, which 

would prevent disconnection and normal 

pitch control. 

This condition, if not corrected, could 

result in further occurrences of reduced 

control of an aeroplane. 

Prompted by these findings, as a temporary 

action to avoid this potential unsafe 

condition, SAAB determined that the potable 

water system should be deactivated. SAAB is 

working on a solution that is expected to 

eliminate the consequences of water spraying 

in the area. 

To address this unsafe condition, EASA 

issued [an] Emergency AD * * * to require 

deactivation of the Potable Water System. 

Since that [EASA] AD was issued, SAAB 

developed a temporary alternative procedure 

for filling, reactivation and continued 

operation of the potable water system. This 

procedure includes a visual inspection to 

make sure that there is no water spray in the 

lower part of the forward fuselage (Zone 116) 

during refilling of the potable water. 

For the reasons described above, this 

[EASA] AD is revised to allow application of 

the alternative filling procedure of the 

Potable Water System. 

This [EASA] AD is still considered to be 

an interim action and further [EASA] AD 

action may follow. 

You may examine the MCAI in the 

AD docket on the Internet at http://

www.regulations.gov/#!documentDetail;

D=FAA-2014-0056-0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM (79 

FR 10433, February 25, 2014) or on the 

determination of the cost to the public. 

‘‘Contacting the Manufacturer’’ 

Paragraph in This AD 

Since late 2006, we have included a 

standard paragraph titled ‘‘Airworthy 

Product’’ in all MCAI ADs in which the 

FAA develops an AD based on a foreign 

authority’s AD. 

The MCAI or referenced service 

information in an FAA AD often directs 

the owner/operator to contact the 

manufacturer for corrective actions, 

such as a repair. Briefly, the Airworthy 

Product paragraph allowed owners/

operators to use corrective actions 

provided by the manufacturer if those 

actions were FAA-approved. In 

addition, the paragraph stated that any 

actions approved by the State of Design 

Authority (or its delegated agent) are 

considered to be FAA-approved. 

In the NPRM (79 FR 10433, February 

25, 2014), we proposed to prevent the 

use of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include a design approval holder 

(DAH) with State of Design Authority 

design organization approval (DOA), as 

applicable, to refer to a DAH authorized 

to approve required repairs for the 

proposed AD. 

No comments were provided to the 

NPRM (79 FR 10433, February 25, 2014) 

about these proposed changes. However, 

a comment was provided for another 

NPRM, Directorate Identifier 2012–NM– 

101–AD (78 FR 78285, December 26, 

2013), in which the commenter stated 

the following: ‘‘The proposed wording, 

being specific to repairs, eliminates the 

interpretation that Airbus messages are 

acceptable for approving minor 

deviations (corrective actions) needed 

during accomplishment of an AD 

mandated Airbus service bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed 

that paragraph and retitled it 

‘‘Contacting the Manufacturer.’’ This 

paragraph now clarifies that for any 

requirement in this AD to obtain 

corrective actions from a manufacturer, 

the action must be accomplished using 

a method approved by the FAA, the 

European Aviation Safety Agency 

(EASA), or Saab AB, Saab Aerosystems’ 

EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that does not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility previously afforded by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the Airworthiness 

Directive Implementation Aviation 

Rulemaking Committee to increase 

flexibility in complying with ADs by 

identifying those actions in 

manufacturers’ service instructions that 

are ‘‘Required for Compliance’’ with 

ADs. We continue to work with 

manufacturers to implement this 

recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to the NPRM 

discussed previously, Directorate 

Identifier 2012–NM–101–AD (78 FR 

78285, December 26, 2013), pointed out 

that in many cases the foreign 

manufacturer’s service bulletin and the 

foreign authority’s MCAI might have 

been issued some time before the FAA 

AD. Therefore, the DOA might have 

provided U.S. operators with an 

approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

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Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations 45339 

Based on these comments, we 

removed the requirement that the DAHprovided repair specifically refer to this 

AD. Before adopting such a 

requirement, the FAA will coordinate 

with affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in this AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. We also 

have decided not to include a generic 

reference to either the ‘‘delegated agent’’ 

or ‘‘DAH with State of Design Authority 

design organization approval,’’ but 

instead we have provided the specific 

delegation approval granted by the State 

of Design Authority for the DAH in the 

Contacting the Manufacturer paragraph 

of this AD. 

Conclusion 

We reviewed the relevant data 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 

10433, February 25, 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 10433, 

February 25, 2014). 

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 1 

airplane of U.S. registry. 

We also estimate that it will take 

about 1 work-hour per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Required parts will cost 

$0 per product. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $85, or $85 per product. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this 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 the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov/#!docketDetail;D=FAA-2014-0056; 

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 street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

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): 

2014–15–04 Saab AB, Saab Aerosystems: 

Amendment 39–17906. Docket No. 

FAA–2014–0056; Directorate Identifier 

2013–NM–160–AD. 

(a) Effective Date 

This AD becomes effective September 9, 

2014. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Saab AB, Saab 

Aerosystems Model SAAB 2000 airplanes, 

certificated in any category, serial numbers 

004 through 016 inclusive, 018, 022, 023, 

024, 026, 029, 031, 032, 033, 035 through 039 

inclusive, 041 through 044 inclusive, 046, 

047, 048, 051, and 053 through 063 inclusive. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 38, Water/Waste. 

(e) Reason 

This AD was prompted by a report of 

rudder pedal restriction which was the result 

of water leakage at the inlet tubing for an inline heater in the lower part of the forward 

fuselage. We are issuing this AD to prevent 

rudder pedal restriction due to the pitch 

control mechanism becoming frozen as the 

result of water spray, which could prevent 

disconnection and normal pitch control, and 

consequently result in reduced 

controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Deactivation of Potable Water System 

Within 30 days after the effective date of 

this AD, deactivate the potable water system, 

in accordance with the Accomplishment 

Instructions of Saab Service Bulletin 2000– 

38–010, dated July 12, 2013. 

(h) Alternative to Deactivation of Potable 

Water System 

As an alternative, or subsequent, to the 

action required by paragraph (g) of this AD, 

during each filling of the potable water 

system after the effective date of this AD, 

accomplish the temporary filling procedure, 

in accordance with the instructions in Saab 

Service Newsletter SN 2000–1304, Revision 

01, dated September 10, 2013, including 

Attachment 1 Engineering Statement to 

Operator 2000PBS034334, Issue A, dated 

September 9, 2013. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANM–116, 

International Branch, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

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45340 Federal Register / Vol. 79, No. 150 / Tuesday, August 5, 2014 / Rules and Regulations 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Shahram Daneshmandi, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1112; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: For any 

requirement in this AD to obtain corrective 

actions from a manufacturer, the action must 

be accomplished using a method approved 

by the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

the European Aviation Safety Agency 

(EASA); or Saab AB, Saab Aerosystems’ 

EASA Design Organization Approval (DOA). 

If approved by the DOA, the approval must 

include the DOA-authorized signature. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2013–0172R1, dated September 6, 

2013, for related information. This MCAI 

may be found in the AD docket on the 

Internet at http://www.regulations.gov/#

!documentDetail;D=FAA-2014-0056-0002. 

(k) 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) Saab Service Bulletin 2000–38–010, 

dated July 12, 2013. 

(ii) Saab Service Newsletter SN 2000–1304, 

Revision 01, dated September 10, 2013, 

including Attachment 1 Engineering 

Statement to Operator 2000PBS034334 Issue 

A, dated September 9, 2013. 

(3) For service information identified in 

this AD, contact Saab AB, Saab Aerosystems, 

SE–581 88, Linko ̈ping, Sweden; telephone 

+46 13 18 5591; fax +46 13 18 4874; email 

saab2000.techsupport@saabgroup.com; 

Internet http://www.saabgroup.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 13, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–17315 Filed 8–4–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0268; Directorate 

Identifier 2011–NM–129–AD; Amendment 

39–17914; AD 2014–15–12] 

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 all The 

Boeing Company Model 737–600, –700, 

–700C, –800, –900 and –900ER series 

airplanes. This AD was prompted by 

reports of incorrectly installed bolts 

common to the rear spar termination 

fitting on the horizontal stabilizer. This 

AD requires inspecting for a serial 

number that starts with the letters 

‘‘SAIC’’ on the left- and right-side 

horizontal stabilizer identification plate; 

inspecting for correct bolt protrusion 

and chamfer of the bolts of the rear spar 

termination fitting of the horizontal 

stabilizer, if necessary; inspecting to 

determine if certain bolts are installed, 

if necessary; and doing related 

investigative and corrective actions if 

necessary. We are issuing this AD to 

prevent loss of structural integrity of the 

horizontal stabilizer attachment and loss 

of control of the airplane. 

DATES: This AD is effective September 9, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 9, 2014. 

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 by searching for 

and locating Docket No. FAA–2012– 

0268; 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: 

Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

WA 98057–3356; phone: 425–917–6440; 

fax: 425–917–6590; email: 

nancy.marsh@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a second supplemental 

notice of proposed rulemaking (SNPRM) 

to amend 14 CFR part 39 by adding an 

AD that would apply to all The Boeing 

Company Model 737–600, –700, –700C, 

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

The second SNPRM published in the 

Federal Register on December 9, 2013 

(78 FR 73744). We preceded the second 

SNPRM with a first SNPRM that 

published in the Federal Register on 

March 7, 2013 (78 FR 14734). We 

preceded the first SNPRM with a notice 

of proposed rulemaking (NPRM) that 

published in the Federal Register on 

March 20, 2012 (77 FR 16188). 

The NPRM proposed to require 

inspecting for a serial number that starts 

with the letters ‘‘SAIC’’ on the left- and 

right-side horizontal stabilizer 

identification plate; a detailed 

inspection for correct bolt protrusion 

and chamfer of the termination fitting 

bolts of the horizontal stabilizer rear 

spar, if necessary; inspecting to 

determine if certain bolts are installed, 

if necessary, and related investigative 

and corrective actions if necessary. The 

NPRM also proposed to require 

repetitive inspections for cracking of the 

termination fitting at certain bolt 

locations, and repair if necessary. The 

NPRM was prompted by reports of 

incorrectly installed bolts common to 

the rear spar termination fitting on the 

horizontal stabilizer. The first SNPRM 

revised the NPRM by adding airplanes 

to the applicability. The second SNPRM 

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