Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 70211 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to XtremeAir GmbH 

Model XA42 airplanes, all serial numbers, 

that: 

(1) Are certificated in any category; and 

(2) have engine mount part number (P/N) 

XA42–7120–151 (manufactured by SzelTech), all serial numbers up to and including 

036, installed. 

(d) Subject 

Air Transport Association of America 

(ATA) Code 71: Power Plant. 

(e) Reason 

This AD was prompted by mandatory 

continuing airworthiness information (MCAI) 

issued by the aviation authority of another 

country to identify and correct an unsafe 

condition on an aviation product. The MCAI 

describes the unsafe condition as cracks in a 

weld seam between the lower left landing 

gear attachment bearing and the lower engine 

mount to the firewall attachment plate. We 

are issuing this AD to prevent failure of the 

engine mounts, which could cause reduced 

structural integrity of the airplane and could 

result in engine separation. 

(f) Actions and Compliance 

Unless already done, do the following 

actions specified in paragraphs (f)(1) through 

(f)(3) of this AD. 

(1) Before further flight after November 25, 

2013 (the effective date of this AD) inspect 

the welds on the engine mount part number 

(P/N) XA42–7120–151 (manufactured by 

Szel-Tech) for cracks following the 

Accomplishment Instructions in XtremeAir 

GmbH Mandatory Service Bulletin SB–2013– 

008, Ausgabe (English translation: Version) 

A.03, dated October 25, 2013. The 

replacement required in paragraph (f)(2) or 

(f)(3) of this AD may be done instead of the 

inspection provided it is done before further 

flight. 

(2) If, during the inspection required in 

paragraph (f)(1) of this AD, a crack is found, 

before further flight, replace the engine 

mount following the Accomplishment 

Instructions in XtremeAir GmbH Mandatory 

Service Bulletin SB–2013–008, Ausgabe 

(English translation: Version) A.03, dated 

October 25, 2013. 

(3) Unless the engine mount P/N XA42– 

7120–151 is replaced with a serviceable part 

as specified in paragraph (f)(2) of this AD, 

within the next 10 hours TIS after November 

25, 2013 (the effective date of this AD), 

replace the engine mount following the 

Accomplishment Instructions in XtremeAir 

GmbH Mandatory Service Bulletin SB–2013– 

008, Ausgabe (English translation: Version) 

A.03, dated October 25, 2013. Acrobatic 

flight is prohibited during these 10 hours. 

(g) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

FAA, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. Send information to 

ATTN: Karl Schletzbaum, Aerospace 

Engineer, FAA, Small Airplane Directorate, 

901 Locust, Room 301, Kansas City, Missouri 

64106; telephone: (816) 329–4123; fax: (816) 

329–4090; email: karl.schletzbaum@faa.gov. 

Before using any approved AMOC on any 

airplane to which the AMOC applies, notify 

your appropriate principal inspector (PI) in 

the FAA Flight Standards District Office 

(FSDO), or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(h) Special Flight Permit 

Special flight permits are prohibited for 

this AD. 

(i) Related Information 

Refer to MCAI European Aviation Safety 

Agency (EASA) AD No.: 2013–0264–E, dated 

October 29, 2013, for related information. 

You may examine the MCAI on the Internet 

at http://www.regulations.gov by searching 

for and locating it in Docket No. FAA–2013– 

0998. 

(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) XtremeAir GmbH Mandatory Service 

Bulletin SB–2013–008, Ausgabe (English 

translation: Version) A.03, dated October 25, 

2013. 

(ii) Reserved. 

(3) For XtremeAir GmbH service 

information identified in this AD, contact 

XtremeAir GmbH, Harzstrasse 2, D–39444 

Hecklingen, Germany; phone: +49 39267 

60999 0; fax: +49 39267 60999 20; email: 

airworthiness@xtremeair.de; Internet: http://

www.xtremeair.de. 

(4) You may view 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. 

(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 Kansas City, Missouri, on 

November 15, 2013. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–27920 Filed 11–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0334; Directorate 

Identifier 2013–NM–027–AD; Amendment 

39–17671; AD 2013–23–16] 

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 757 airplanes. 

This AD was prompted by a report of a 

broken forward support fitting at the 

inboard track of the inboard flap. This 

AD requires repetitive inspections of the 

forward support fitting assemblies of the 

inboard track of the left and right 

inboard flaps for cracking, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

cracking of the forward support fitting 

assembly, which could result in loss of 

inboard flap control and subsequent loss 

of airplane control. 

DATES: This AD is effective December 

30, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 30, 2013. 

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 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 


emcdonald on DSK67QTVN1PROD with RULES
70212 Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 

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, 

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 notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 by adding an AD that would 

apply to the specified products. The 

NPRM published in the Federal 

Register on April 22, 2013 (78 FR 

23694). The NPRM proposed to require 

repetitive inspections of the forward 

support fitting assemblies of the inboard 

track of the left and right inboard flaps 

for cracking, 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 23964, 

April 22, 2013) and the FAA’s response 

to each comment. 

Supportive Comment 

Boeing stated that it concurs with the 

NPRM (78 FR 23964, April 22, 2013). 

Request To Provide Justification for AD 

Action 

FedEx requested further data and 

justification for this AD action. FedEx 

stated that it expected a single data 

point (i.e., the one failure of a forward 

support fitting assembly) would 

represent an anomaly. FedEx asked if a 

root cause analysis was done to 

determine whether the single failure 

was an anomaly induced during 

manufacture or operator maintenance 

before proceeding with service 

information and NPRM development. 

We find that clarification is necessary. 

Boeing Special Attention Service 

Bulletin 757–57–0071, dated September 

12, 2012, states that the cracking 

occurred at a compound radius in the 

part. This design detail, which occurs 

on each part having the part number 

identified in that service bulletin, has 

been identified as an area of high stress 

concentration and a likely location for 

fatigue cracking to initiate at a relatively 

low number of flight cycles. The 

airplane event, as detailed in that 

service bulletin, occurred at 22,328 

flight cycles and both components of the 

forward support fitting assembly were 

found to be completely cracked through. 

Therefore, the occurrence of cracking in 

this part at this location is likely to 

occur on other airplanes, and cannot be 

considered an anomaly. Since these 

cracked fittings result in an unsafe 

condition and we determined that this 

unsafe condition is likely to exist or 

develop in other products of the same 

type design, we determined that this AD 

rulemaking is necessary. We have not 

changed this final rule in this regard. 

Request for Procedures To Apply a 

Chemical Conversion Coating 

American Airlines (AAL) 

recommended that a step be added 

between steps 10 and 11 in sheet 3 of 

6 of the Forward Support Fitting 

Assembly Replacement figures of 

Boeing Special Attention Service 

Bulletin 757–57–0071, dated September 

12, 2012. The additional step would 

specify applying a chemical conversion 

coating after match drilling holes as part 

of the fitting assembly replacement 

process. AAL noted that in the Material 

Information of Boeing Special Attention 

Service Bulletin 757–57–0071, dated 

September 12, 2012, chemical 

conversion coating is identified in the 

parts lists, but the Accomplishment 

Instructions section of that service 

bulletin omits the coating. 

We agree that Boeing Special 

Attention Service Bulletin 757–57– 

0071, dated September 12, 2012, does 

not specify applying a chemical 

conversion coating after match drilling 

holes. Boeing specified that the 

installation of the fasteners with sealant, 

as specified in the instructions in the 

service information, provides corrosion 

protection at the fastener locations and 

that application of the chemical 

conversion coating is not required. Once 

we issue this AD, any person may 

request approval of an alternative 

method of compliance (AMOC) to apply 

alternative corrosion protection coatings 

under the provisions of paragraph (i) of 

this final rule. We have not changed this 

final rule in this regard. 

Request To Delay AD To Address Parts 

Availability 

AAL requested that the FAA ensure 

ample parts availability before releasing 

the AD. AAL stated that there is a lead 

time of 160 days for the fitting assembly 

and suggested that the NPRM (78 FR 

23964, April 22, 2013) be revised to 

allow for manufacture of parts and 

provide material specifications and part 

dimensions. FedEx stated that about 

seven fitting assemblies are due to be in 

stock in July 2013. 

We disagree to revise or delay this 

final rule. In developing this final rule, 

we coordinated with the manufacturer 

an appropriate compliance time to 

address the unsafe condition in a timely 

manner and take parts availability into 

consideration. We have not changed this 

final rule in this regard. 

Conclusion 

We reviewed the relevant data, 

considered the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

as proposed except for minor editorial 

changes. We have determined that these 

minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (78 FR 

23964, April 22, 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 23964, 

April 22, 2013). 

Costs of Compliance 

We estimate that this AD affects 690 

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 

High-frequency eddy current inspection.11 work-hours × $85 per 

hour = $935, per inspection cycle.

None .................................. $935, per inspection cycle $645,150, per inspection 

cycle. 

We estimate the following costs to do 

any necessary replacements that would 

be required based on the results of the 

inspection. We have no way of 

determining the number of aircraft that 

might need this replacement: 


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Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 70213 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Replacement .................................. 7 work-hours × $85 per hour = $595, per assembly $10,000 $10,595, per assembly. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. Subtitle VII: 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

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

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2013–23–16 The Boeing Company: 

Amendment 39–17671; Docket No. 

FAA–2013–0334; Directorate Identifier 

2013–NM–027–AD. 

(a) Effective Date 

This AD is effective December 30, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to all The Boeing 

Company Model 757–200, –200PF, –200CB, 

and –300 series airplanes, certificated in any 

category. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 5753, Trailing edge flaps. 

(e) Unsafe Condition 

This AD was prompted by a report of a 

broken forward support fitting at the inboard 

track of the inboard flap. We are issuing this 

AD to detect and correct cracking of the 

forward support fitting assembly, which 

could result in loss of inboard flap control 

and subsequent loss of airplane control. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspection and Corrective Action 

Except as provided by paragraph (h) of this 

AD, at the applicable time specified in 

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

Special Attention Service Bulletin 757–57– 

0071, dated September 12, 2012: Do a high 

frequency eddy current (HFEC) inspection for 

cracking in the forward support fitting 

assemblies of the inboard track of the left and 

right inboard flaps, and do all applicable 

corrective actions, in accordance with 

paragraph 3.B.2. of the Accomplishment 

Instructions of Boeing Special Attention 

Service Bulletin 757–57–0071, dated 

September 12, 2012. Do all applicable 

corrective actions before further flight. 

Thereafter, repeat the inspections at intervals 

not to exceed 6,000 flight cycles, except as 

required by paragraphs (g)(1) and (g)(2) of 

this AD. 

(1) For Group 1 airplanes, as identified in 

Boeing Special Attention Service Bulletin 

757–57–0071, dated September 12, 2012, on 

which any forward support fitting assembly 

is replaced: Do the next inspection before 

15,000 flight cycles have accumulated on that 

assembly. 

(2) For Group 2 airplanes, as identified in 

Boeing Special Attention Service Bulletin 

757–57–0071, dated September 12, 2012, on 

which any forward support fitting assembly 

is replaced: Do the next inspection before 

18,000 flight cycles have accumulated on that 

assembly. 

(h) Exceptions to the Service Information 

(1) Where Boeing Special Attention Service 

Bulletin 757–57–0071, dated September 12, 

2012, specifies compliance times ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance times ‘‘after the 

effective date of this AD.’’ 

(2) Paragraphs 3.B.1. and 3.B.3. of the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 757–57– 

0071, dated September 12, 2012, are not 

required by this AD. 

(i) 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 (j) 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. 

(j) Related Information 

For more information about this AD, 

contact Nancy Marsh, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: (425) 917–6440; fax: (425) 917–6590; 

email: nancy.marsh@faa.gov. 


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70214 Federal Register / Vol. 78, No. 227 / Monday, November 25, 2013 / Rules and Regulations 

(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 the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 757–57–0071, dated September 12, 

2012. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Ave 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 

November 6, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–27843 Filed 11–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0461; Directorate 

Identifier 2012–NM–169–AD; Amendment 

39–17670; AD 2013–23–15] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2009–06– 

02, which applied to certain The Boeing 

Company Model 747–100, 747–100B, 

747–100B SUD, 747–200B, 747–200C, 

747–200F, 747–300, 747–400, 747SR, 

and 747SP series airplanes. AD 2009– 

06–02 required repetitive inspections 

for skin cracks at the shear tie end 

fastener locations of the fuselage frames, 

and repair of cracks if necessary. This 

new AD also requires repetitive 

inspections for skin cracks next to the 

shear tie on airplanes with certain 

existing repair doublers, and corrective 

actions if necessary. This AD also 

revises the applicability to include 

additional airplanes. This AD was 

prompted by additional cracking found 

on an airplane not affected by AD 2009– 

06–02. We are issuing this AD to detect 

and correct fatigue cracks in the fuselage 

skin that can propagate and grow, and 

result in reduced structural integrity 

and sudden decompression of the 

airplane in flight. 

DATES: This AD is effective December 

30, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of December 30, 2013. 

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, Washington. 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 

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: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

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

Washington 98057–3356; phone: 425– 

917–6577; fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–06–02, 

Amendment 39–15838 (74 FR 11013, 

March 16, 2009). AD 2009–06–02 

applied to the specified products. The 

NPRM published in the Federal 

Register on June 3, 2013 (78 FR 33012). 

The NPRM proposed to continue to 

require repetitive inspections for skin 

cracks at the shear tie end fastener 

locations of the fuselage frames, and 

repair of cracks if necessary. The NPRM 

also proposed to require repetitive 

inspections for skin cracks next to the 

shear tie on airplanes with certain 

existing repair doublers, and corrective 

actions if necessary. The NPRM also 

proposed to revise the applicability to 

include additional airplanes. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (78 FR 33012, 

June 3, 2013) and the FAA’s response to 

each comment. 

Request To Revise Repetitive Inspection 

Type 

Boeing requested that we revise 

paragraph (h) of the NPRM (78 FR 

33012, June 3, 2013) to correct the 

required inspection method for the 

repetitive inspections. The NPRM 

specified repeating the ‘‘external 

detailed inspection’’ at the times 

specified in table 4 or table 5 of Boeing 

Alert Service Bulletin 747–53A2682, 

Revision 1, dated May 24, 2012. Boeing 

noted however that the compliance 

times in those tables are for internal 

high frequency eddy current (HFEC) 

inspection. 

We agree with the request. Paragraph 

(h) of this AD requires an internal HFEC 

inspection; the inspections that must be 

repeated are also internal HFEC 

inspections. We have revised paragraph 

(h) in this final rule to specify that the 

inspection to be repeated is an internal 

HFEC inspection. 

Request To Revise Description of 

Unsafe Condition 

Boeing requested that we revise the 

description of the unsafe condition to 

clarify that the subject of the unsafe 

condition is the fuselage area—not the 

frame shear ties, as stated in the NPRM 

(78 FR 33012, June 3, 2013). 

We agree with the request and 

rationale. We have revised paragraph (e) 

in this final rule to explain that the 

fuselage skin—not the ties themselves— 

is subject to widespread fatigue damage. 

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 


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