52416 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Inspections 

Before the accumulation of 24,000 total 

flight cycles since first flight of the airplane, 

or within 30 days after the effective date of 

this AD, whichever occurs later, do the 

actions specified in paragraph (g)(1) or (g)(2) 

of this AD. 

(1) Do a general visual inspection for a 

missing fastener between the two fasteners at 

fuselage frame (FR) 24 between stringer 25 

and stringer 26 right-hand side, in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–53–1247, Revision 01, dated 

October 15, 2012. 

(i) If the fastener is not missing, no further 

action is required by paragraph (g) of this AD. 

(ii) If the fastener is missing, before further 

flight, do the actions required by paragraph 

(g)(2) of this AD. 

(2) Do a rototest inspection for cracking of 

the two adjacent fastener holes at 

fuselage FR 24 between stringer 25 and 

stringer 26 right-hand side, in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A320–53–1247, 

dated July 15, 2011; or Airbus Mandatory 

Service Bulletin A320–53–1247, Revision 01, 

dated October 15, 2012. 

(h) Repair 

(1) If, during the rototest inspection 

specified by paragraph (g)(2) of this AD, any 

crack is found, before further flight, repair 

using a method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the European 

Aviation Safety Agency (EASA) (or its 

delegated agent). 

(2) If, during the rototest inspection 

specified by paragraph (g)(2) of this AD, no 

crack is found, before the accumulation of 

24,000 total flight cycles since first flight of 

the airplane, or within 30 days after the 

effective date of this AD, whichever occurs 

later: Modify fuselage FR 24 between stringer 

25 and stringer 26 right-hand side, in 

accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A320– 

53–1247, dated July 15, 2011; or Airbus 

Mandatory Service Bulletin A320–53–1247, 

Revision 01, dated October 15, 2012. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, 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 International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–1405; 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) 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. 

(j) Related Information 

Refer to mandatory continuing 

airworthiness information (MCAI) EASA 

Airworthiness Directive 2011–0229, dated 

December 6, 2011, for related information. 

The MCAI may be viewed on the Internet at 

http://ad.easa.europa.eu/ad/2011–0229. 

EASA ADs are at http://ad.easa.europa.eu/. 

(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) Airbus Mandatory Service Bulletin 

A320–53–1247, Revision 01, dated October 

15, 2012. 

(ii) Airbus Service Bulletin A320–53–1247, 

dated July 15, 2011. 

(3) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. 

(4) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

(5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http:// 

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

2, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19459 Filed 8–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0092; Directorate 

Identifier 2012–NM–067–AD; Amendment 

39–17560; AD 2013–16–22] 

RIN 2120–AA64 

Airworthiness Directives; Embraer S.A. 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Embraer S.A. Model ERJ 170 and ERJ 

190 airplanes. This AD was prompted 

by reports of chafing between the 

auxiliary power unit (APU) electronic 

starter controller (ESC) power cables 

and the airplane tail cone firewall. This 

AD requires a detailed inspection for 

damage to the insulation and inner 

conductors of the APU ESC power 

cables, installing a new grommet 

support in the tail cone firewall, and 

corrective actions if necessary. We are 

issuing this AD to detect and correct 

damage to the APU ESC power cable 

harness, which if not corrected, could 

result in reduced structural integrity of 

the fuselage and empennage in the event 

of fire penetration through the firewall. 

DATES: This AD becomes effective 

September 27, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 27, 2013. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2768; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on February 22, 2013 (78 FR 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 52417 

12256). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The Ageˆncia Nacional de 

Aviac ̧a ̃o Civil (ANAC), which is the 

airworthiness authority for Brazil, has 

issued Brazilian Airworthiness 

Directives 2012–03–03 and 2012–03–04, 

both effective April 13, 2012 (referred to 

after this as the Mandatory Continuing 

Airworthiness Information, or ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

It has been found the occurrences of 

chafing between the Auxiliary Power Unit 

(APU) Electronic Starter Controller (ESC) 

power cables (harness W205) and the 

airplane tail cone firewall due to the 

grommet installed in the tail cone firewall 

moves out of its place. This condition, if not 

corrected, may result in reduced structural 

integrity of the fuselage and empennage in an 

event of fire penetration through the firewall. 

* * * 

The required actions include a 

detailed inspection for damage to the 

harness insulation and inner conductors 

of the APU ESC power cables, installing 

a new grommet support in the tail cone 

firewall, and corrective actions if 

necessary. Corrective actions include 

repairing the harness W205 insulation 

or replacing the harness W205 of the 

APU ESC power cables with a new 

harness. You may obtain further 

information by examining the MCAI in 

the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

have considered the comments received. 

Request To Add Credit for Actions 

Accomplished in Accordance With 

Previous Service Information 

Embraer S.A. requested that we revise 

the NPRM (78 FR 12256, February 22, 

2013) to allow credit for work done 

prior to the effective date of the 

proposed AD using Embraer Service 

Bulletin 170–53–0093, dated February 

28, 2011; Embraer Service Bulletin 190– 

53–0054, dated February 28, 2011; or 

Embraer Service Bulletin 190LIN–53– 

0059, dated March 29, 2011; which are 

now all at Revision 01, dated March 16, 

2012. Embraer notes that the 

instructions contained in the original 

issue of the service information 

combined with the instructions Embraer 

has provided to operators on a case-bycase basis are equivalent. 

We disagree with the commenter’s 

request because the FAA has no 

familiarity with the individual repair or 

replacement instructions provided by 

Embraer to each operator and cannot 

evaluate them for equivalence to the 

instructions in the required service 

information. The MCAI also does not 

allow credit for work performed using 

previous versions of the service 

information. Operators may apply for an 

alternative method of compliance 

(AMOC) for these actions in accordance 

with the provisions of paragraph (i)(1) of 

this AD. We have not changed the AD 

in this regard. 

Explanation of Additional Changes 

Made to This AD 

We have revised the wording of 

paragraph (g) of this AD, which 

previously required a detailed visual 

inspection instead of a detailed 

inspection. We have also added 

paragraph (h) of this AD, which 

includes the definition of a detailed 

inspection. 

Conclusion 

We reviewed the available data, 

including the comment 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 

12256, February 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 12256, 

February 22, 2013). 

Costs of Compliance 

We estimate that this AD will affect 

253 products of U.S. registry. We also 

estimate that it will take about 15 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $322,575, or 

$1,275 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. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD docket. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Operations office 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: 


emcdonald on DSK67QTVN1PROD with RULES
52418 Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 

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 AD: 

2013–16–22 Embraer S.A: Amendment 39– 

17560. Docket No. FAA–2013–0092; 

Directorate Identifier 2012–NM–067–AD. 

(a) Effective Date 

This airworthiness directive (AD) becomes 

effective September 27, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the airplane models 

identified in paragraphs (c)(1) and (c)(2) of 

this AD. 

(1) Embraer S.A. Model ERJ 170–100 LR, 

–100 STD, –100 SE., and –100 SU airplanes; 

and Model ERJ 170–200 LR, –200 SU, and 

–200 STD airplanes; certificated in any 

category; as identified in Embraer Service 

Bulletin 170–53–0093, Revision 01, dated 

March 16, 2012. 

(2) Embraer S.A. Model ERJ 190–100 STD, 

–100 LR, –100 ECJ, and –100 IGW airplanes; 

and Model ERJ 190–200 STD, –200 LR, and 

–200 IGW airplanes; certificated in any 

category; as identified in Embraer Service 

Bulletin 190–53–0054, Revision 01, dated 

March 16, 2012; and Embraer Service 

Bulletin 190LIN–53–0059, Revision 01, dated 

March 16, 2012. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of 

chafing between the auxiliary power unit 

(APU) electronic starter controller (ESC) 

power cables and the airplane tail cone 

firewall. We are issuing this AD to detect and 

correct damage to the APU ESC power cable 

harness, which could result in reduced 

structural integrity of the fuselage and 

empennage in the event of fire penetration 

through the firewall. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Detailed Inspection, Installation, and 

Corrective Actions 

Within 3,000 flight hours or 18 months 

after the effective date of this AD, whichever 

occurs first: Do a detailed inspection for 

damage to the insulation and inner 

conductors of the APU ESC power cables 

(harness W205), in accordance with the 

Accomplishment Instructions of Embraer 

Service Bulletin 170–53–0093, Revision 01, 

dated March 16, 2012 (for Model ERJ 170 

airplanes); Embraer Service Bulletin 190–53– 

0054, Revision 01, dated March 16, 2012 (for 

Model ERJ 190 airplanes except for Model 

ERJ 190–100 ECJ airplanes); and Embraer 

Service Bulletin 190LIN–53–0059, Revision 

01, dated March 16, 2012 (for Model ERJ 

190–100 ECJ airplanes). 

(1) If no damage is found, before further 

flight, install a new grommet support having 

part number (P/N) 191–21716–003 in the tail 

cone firewall, in accordance with the 

Accomplishment Instructions of Embraer 

Service Bulletin 170–53–0093, Revision 01, 

dated March 16, 2012 (for Model ERJ 170 

airplanes); Embraer Service Bulletin 190–53– 

0054, Revision 01, dated March 16, 2012 (for 

Model ERJ 190 airplanes except for Model 

ERJ 190–100 ECJ airplanes); or Embraer 

Service Bulletin 190LIN–53–0059, Revision 

01, dated March 16, 2012 (for Model ERJ 

190–100 ECJ airplanes). 

(2) If any damage is found during any 

inspection required in paragraph (g) of this 

AD that affects only the insulation of harness 

W205 of the APU ESC power cables: Before 

further flight, repair the insulation and install 

a new grommet support having P/N 191– 

21716–003 in the tail cone firewall, in 

accordance with the Accomplishment 

Instructions of Embraer Service Bulletin 170– 

53–0093, Revision 01, dated March 16, 2012 

(for Model ERJ 170 airplanes); Embraer 

Service Bulletin 190–53–0054, Revision 01, 

dated March 16, 2012 (for Model ERJ 190 

airplanes except for Model ERJ 190–100 ECJ 

airplanes); or Embraer Service Bulletin 

190LIN–53–0059, Revision 01, dated March 

16, 2012 (for Model ERJ 190–100 ECJ 

airplanes). 

(3) If any damage is found during any 

inspection required in paragraph (g) of this 

AD that affects the insulation of harness 

W205 of the APU ESC power cables and the 

inner conductors: Before further flight, 

replace the harness with a new harness and 

install a new grommet support having P/N 

191–21716–003 in the tail cone firewall, in 

accordance with the Accomplishment 

Instructions of Embraer Service Bulletin 170– 

53–0093, Revision 01, dated March 16, 2012 

(for Model ERJ 170 airplanes); Embraer 

Service Bulletin 190–53–0054, Revision 01, 

dated March 16, 2012 (for Model ERJ 190 

airplanes except for Model ERJ 190–100 ECJ 

airplanes); or Embraer Service Bulletin 

190LIN–53–0059, Revision 01, dated March 

16, 2012 (for Model ERJ 190–100 ECJ 

airplanes). 

(h) Definition of Detailed Inspection 

For the purpose of this AD, a detailed 

inspection is: An intensive examination of a 

specific item, installation or assembly to 

detect damage, failure or irregularity. 

Available lighting is normally supplemented 

with a direct source of good lighting at an 

intensity deemed appropriate. Inspection 

aids such as mirrors, magnifying lenses, etc., 

may be necessary. Surface cleaning and 

elaborate access procedures may be required. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Cindy Ashforth, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone: (425) 227–2768; 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) 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. 

(j) Related Information 

Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Brazilian 

Airworthiness Directives 2012–03–03 and 

2012–03–04, both effective April 13, 2012, 

for related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov. 

(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) Embraer Service Bulletin 170–53–0093, 

Revision 01, dated March 16, 2012. 

(ii) Embraer Service Bulletin 190–53–0054, 

Revision 01, dated March 16, 2012. 

(iii) Embraer Service Bulletin 190LIN–53– 

0059, Revision 01, dated March 16, 2012. 

(3) For service information identified in 

this AD, contact Embraer S.A., Technical 

Publications Section (PC 060), Av. Brigadeiro 

Faria Lima, 2170—Putim—12227–901 Sa ̃o 

Jose dos Campos—SP—BRASIL; telephone 

+55 12 3927–5852 or +55 12 3309–0732; fax 

+55 12 3927–7546; email distrib@

embraer.com.br; Internet http://

www.flyembraer.com. 

(4) You may review copies of the 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 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 164 / Friday, August 23, 2013 / Rules and Regulations 52419 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on August 

2, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19463 Filed 8–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0931; Directorate 

Identifier 2011–NM–128–AD; Amendment 

39–17555; AD 2013–16–17] 

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 727, 727C, 727– 

100, 727–100C, 727–200, and 727–200F 

series airplanes. This AD was prompted 

by a structural re-evaluation by the 

manufacturer, which identified 

elements within the wing trailing edge 

flap area that qualify as structural 

significant items (SSIs). This AD 

requires revising the maintenance 

inspection program to include 

inspections that will give no less than 

the required damage tolerance rating 

(DTR) for certain SSIs, and repairing any 

cracked structure. We are issuing this 

AD to detect and correct fatigue 

cracking of the wing trailing edge 

structure, which could result in 

compromised structural integrity of the 

airplane. 

DATES: This AD is effective September 

27, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of September 27, 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 

review copies of the 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 

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 include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on September 6, 2012 (77 FR 

54856). That NPRM proposed to require 

revising the maintenance inspection 

program to include inspections that will 

give no less than the required damage 

tolerance rating for certain SSIs, and 

repairing cracked structure. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the proposal (77 FR 54856, 

September 6, 2012) and the FAA’s 

response to each comment. 

Request To Add Compliance Time 

Allowance 

Boeing requested that we add a 

compliance time allowance to paragraph 

(c)(2) of the NPRM (77 FR 54856, 

September 6, 2012) for the 

determination of the alternative 

inspection requirements for each SSI 

affected by a repair or alteration that 

prohibits the ability to accomplish the 

inspections required by paragraph (g) of 

the NPRM. Boeing requested that we 

add to paragraph (c) of this AD a 

compliance period of 12 months and 

associated language similar to that in 

paragraph (j) of AD 2008–11–03, 

Amendment 39–15525 (73 FR 29407, 

May 21, 2008). Boeing justified its 

request by stating that the following 

ADs allow up to 12 months to determine 

the alternative inspection requirements 

should a repair or alteration prohibit the 

required inspection, and that including 

similar language in the NPRM will assist 

the operator. 

• Paragraph (e) of AD 98–11–03 Rl, 

Amendment 39–10983 (64 FR 989, 

January 7, 1999). 

• Paragraph (j) of AD 2008–11–03, 

Amendment 39–15525 (73 FR 29407, 

May 21, 2008). 

• Paragraph (i) of AD 2008–09–13, 

Amendment 39–15494 (73 FR 24164, 

May 2, 2008). 

We partially agree with the 

commenter’s request. We agree with 

adding an allowance similar to that 

requested by the commenter because 

operators might have existing repairs 

that affect the ability to accomplish the 

SSI inspections. We disagree with 

adding that allowance to paragraph 

(c)(2) of this AD. That paragraph is an 

applicability provision. We have added 

a new paragraph (h) to this AD to 

address SSIs that have been repaired or 

altered before the effective date of this 

AD such that the repair or design 

change affects the ability to accomplish 

the actions required by paragraph (g) of 

this AD. We have reidentified 

subsequent paragraphs accordingly. 

Request To Add Repetitive Inspection 

Wording 

Boeing requested that we revise 

paragraph (g)(2) of the NPRM (77 FR 

54856, September 6, 2012) to add the 

following wording: 

Repeat the applicable inspection thereafter 

at the intervals necessary to obtain the 

required DTR specified in Boeing Document 

D6–48040–2, Supplemental Structural 

Inspection Document For Model 727 

Airplanes, Appendix A, dated December 

2010. 

Boeing stated that the NPRM does not 

address the repetitive inspection 

requirements after the initial 

inspections are accomplished. Boeing 

requested the wording revision in order 

to maintain consistency with the 

wording contained in paragraph (i) of 

AD 2008–11–03, Amendment 39–15525 

(73 FR 29407, May 21, 2008); and 

paragraph (h) of AD 2008–09–13, 

Amendment 39–15494 (73 FR 24164, 

May 2, 2008). 

We do not agree with the commenter’s 

request because the repetitive 

inspection and methodology 

requirements are specified in the DTR 

forms of Boeing Document D6–48040–2, 

Supplemental Structural Inspection 

Document for Model 727 Airplanes, 

Appendix A, dated December 2010. By 


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